
[Federal Register Volume 80, Number 196 (Friday, October 9, 2015)]
[Rules and Regulations]
[Pages 61093-61098]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-25490]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0108; Directorate Identifier 2011-NM-049-AD; 
Amendment 39-18215; AD 2015-15-06]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2003-13-01 for 
certain The Boeing Company Model 767 airplanes. AD 2003-13-01 required 
an inspection to detect cracks and fractures of the outboard hinge 
fitting assemblies on the trailing edge of the inboard main flap, and 
follow-on and corrective actions if necessary. For certain airplanes, 
AD 2003-13-01 required an inspection to determine if a tool runout 
option has been performed in the area. This new AD reduces certain 
compliance times, adds airplanes to the applicability, and provides 
optional terminating action for certain inspections. This AD was 
prompted by reports of hinge assembly fractures found before certain 
required compliance times in AD 2003-13-01. We are issuing this AD to 
prevent the inboard aft flap from separating from the wing and 
potentially striking the airplane, which could result in damage to the 
surrounding structure and potential personal injury.

DATES: This AD is effective November 13, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 13, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of July 
29, 2003 (68 FR 37402, June 24, 2003).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2012-
0108.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2012-
0108; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday,

[[Page 61094]]

except Federal holidays. The AD docket contains this AD, the regulatory 
evaluation, any comments received, and other information. The address 
for the Docket Office (phone: 800-647-5527) is Docket Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: wayne.lockett@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2003-13-01, Amendment 39-13201 (68 
FR 37402, June 24, 2003). AD 2003-13-01 applied to certain The Boeing 
Company Model 767 airplanes. The SNPRM published in the Federal 
Register on September 29, 2014 (79 FR 58294). We preceded the SNPRM 
with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on February 9, 2012 (77 FR 6685). The NPRM proposed to 
continue to require an inspection to detect cracks and fractures of the 
outboard hinge fitting assemblies on the trailing edge of the inboard 
main flap, and follow-on and corrective actions if necessary. For 
certain airplanes, the NPRM proposed to continue to require inspecting 
to determine if a tool runout option has been performed in the area. 
The NPRM also proposed to reduce a certain compliance time and add 
airplanes to the applicability. The NPRM provided optional terminating 
action for certain inspections. The NPRM was prompted by reports of 
hinge assembly fractures found before certain required compliance times 
in AD 2003-13-01. The SNPRM revised the NPRM by reducing repetitive 
inspection intervals for certain airplanes and limiting the inspection 
area. We are issuing this AD to prevent the inboard aft flap from 
separating from the wing and potentially striking the airplane, which 
could result in damage to the surrounding structure and potential 
personal injury.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the SNPRM (79 
FR 58294, September 29, 2014) and the FAA's response to each comment.

Support for the SNPRM (79 FR 58294, September 29, 2014)

    Boeing concurred with the contents of the SNPRM (79 FR 58294, 
September 29, 2014).

Requests To Remove Certain Provisions for Spare Parts

    American Airlines and UPS requested that we revise the SNPRM (79 FR 
58294, September 29, 2014) by removing paragraph (q), because its 
provisions are redundant with the requirements of paragraph (k) of the 
SNPRM.
    We agree with the requests, for the reason provided by the 
commenters. We have removed the referenced paragraph and redesignated 
subsequent paragraphs accordingly.

Request To Clarify Replacement Requirements

    American Airlines requested that we revise the SNPRM (79 FR 58294, 
September 29, 2014) to identify the part numbers for fittings that are 
acceptable for terminating action, but to not require specific removal 
and reinstallation procedures. The commenter added that the design 
change of the fitting--not the installation method--corrects the unsafe 
condition.
    We partially agree with the request. Although we did not identify 
the part numbers, we revised paragraph (o) in this AD to specify only 
the specific step that provides the replacement instructions and 
identifies the part number of the new fittings. Other removal and 
reinstallation actions related to the fitting replacement may be done 
using accepted methods in accordance with the operator's maintenance or 
inspection program.
    We disagree with American Airlines' assertion that only the fitting 
design ``corrects the unsafe condition.'' ADs contain requirements that 
are related to addressing the unsafe condition, as determined by the 
FAA and the design approval holder that developed the service 
information. Therefore, many provisions of ADs address aspects of 
accomplishing the required maintenance that are necessary to prevent 
operators from inadvertently aggravating the unsafe condition or 
introducing new unsafe conditions. As in this case, the replacement 
instructions provided in the referenced service information are 
reasonably related to addressing the unsafe condition.
    As always, operators preferring to use a method other than that 
specified in the referenced service information may request approval 
for an alternative method of compliance and, if approved, may use it 
instead of the procedures specified in the service information.
    We further clarified this action throughout this AD by revising the 
description of the replacement part by specifying ``the inboard main 
flap outboard hinge fittings.''

Effect of Winglets on AD

    Aviation Partners Boeing, United Airlines, Delta Air Lines, and UPS 
requested that the SNPRM (79 FR 58294, September 29, 2014) specify that 
accomplishment of supplemental type certificate (STC) ST01920SE (http:/
/rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect 
the actions in the SNPRM.
    We concur with the request. We have redesignated the introductory 
text of paragraph (c) of the SNPRM (79 FR 58294, September 29, 2014) as 
paragraph (c)(1), and subparagraphs (c)(1) and (c)(2) as (c)(1)(i) and 
(c)(1)(ii), and added new paragraph (c)(2) to this AD to state that 
installation of STC ST01920SE (http://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) does not affect 
the ability to accomplish the actions required by this final rule. 
Therefore, for airplanes on which STC ST01920SE is installed, a 
``change in product'' alternative method of compliance (AMOC) approval 
request is not necessary to comply with the requirements of 14 CFR 
39.17.

Change of Location for Certain Credit Service Information

    We have removed Boeing Alert Service Bulletin 767-57A0079, Revision 
1, dated May 6, 2010, which is referred to for credit for certain 
actions, from paragraph (g)(2) of the proposed AD. Instead, we have 
revised paragraph (p)(1) of this AD to specifically provide credit for 
actions required by paragraph (g)(2) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Service Bulletin 767-57A0079, Revision 1, dated May 6, 2010. We have 
redesignated subsequent paragraphs (including the addition of new 
paragraph (p)(3)) accordingly. This change does not affect the intent 
of paragraph (g)(2) of this AD.

[[Page 61095]]

Change to Retained Credit for Previous Actions Language

    We have revised the wording in paragraph (l) of this AD; this 
change has not changed the intent of that paragraph.

Change to Previous AMOCs Paragraph

    We have added a reference to paragraph (j) of this AD in paragraph 
(q)(4) of this AD to account for any AMOCs that might have been 
approved for the optional action specified in paragraph (j) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM (79 FR 58294, September 29, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM (79 FR 58294, September 29, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 767-57A0079, Revision 2, 
dated March 23, 2012; and Boeing Alert Service Bulletin 767-57A0076, 
Revision 3, dated April 4, 2012. The service information describes 
procedures for repetitive eddy current inspections for cracks or 
fractures of the outboard hinge fitting assemblies on the trailing edge 
of the inboard main flap. The service information also describes 
procedures for replacing the fittings, which would eliminate the need 
for the repetitive inspections. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section of this final rule.

Costs of Compliance

    We estimate that this AD affects 440 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained detailed inspections..  10 work-hours x $85 per              $0  $850 per            $374,000 per
                                  hour = $850 per                          inspection cycle.   inspection cycle.
                                  inspection cycle.
Retained detailed and eddy       13 work-hours x $85 per               0  $1,105 per          $486,200 per
 current inspections.             hour = $1,105 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of airplanes that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                 Action                                Labor cost                  Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement.............................  32 work-hours x $85 per hour =               $45,400          $48,120
                                           $2,720.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), and adding 
the following new AD:


[[Page 61096]]


2015-15-06 The Boeing Company: Amendment 39-18215; Docket No. FAA-
2012-0108; Directorate Identifier 2011-NM-049-AD.

(a) Effective Date

    This AD is effective November 13, 2015.

(b) Affected ADs

    This AD replaces AD 2003-13-01, Amendment 39-13201 (68 FR 37402, 
June 24, 2003).

(c) Applicability

    (1) This AD applies to The Boeing Company airplanes, 
certificated in any category, identified in paragraphs (c)(1)(i) and 
(c)(1)(ii) of this AD.
    (i) Model 767-200, -300, and -300F series airplanes, as 
specified in Boeing Alert Service Bulletin 767-57A0076, Revision 3, 
dated April 4, 2012.
    (ii) Model 767-400ER series airplanes, as specified in Boeing 
Alert Service Bulletin 767-57A0079, Revision 2, dated March 23, 
2012.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/59027f43b9a7486e86257b1d006591ee/$FILE/ST01920SE.pdf) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01920SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of hinge assembly fractures 
found before certain required compliance times on airplanes subject 
to AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003). 
We are issuing this AD to prevent the inboard aft flap from 
separating from the wing and potentially striking the airplane, 
which could result in damage to the surrounding structure and 
potential personal injury.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Inspection, With Revised Service Information

    This paragraph restates the requirements of paragraph (a) of AD 
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with 
revised service information. Perform either a detailed inspection, 
or a detailed inspection plus an eddy current inspection, of the 
outboard hinge fitting assemblies on the trailing edge of the 
inboard main flap to detect cracks and fractures and evidence of a 
tool runout option, as applicable. For the purposes of this AD, a 
detailed inspection is defined as an intensive visual examination of 
a specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.
    (1) For Model 767-200, -300, and -300F series airplanes 
identified in Boeing Service Bulletin 767-57A0076, Revision 1, dated 
March 29, 2001: Inspect before the airplane accumulates 2,700 total 
flight cycles, or within 90 days after July 29, 2003 (the effective 
date of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 
2003)), whichever occurs later, in accordance with Boeing Service 
Bulletin 767-57A0076, Revision 1, dated March 29, 2001; or the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0076, Revision 3, dated April 4, 2012. As of the effective date 
of this AD, only Boeing Service Bulletin 767-57A0076, Revision 3, 
dated April 4, 2012, may be used for the inspection.
    (2) For Model 767-400ER series airplanes identified in Boeing 
Alert Service Bulletin 767-57A0079, dated June 20, 2002: Inspect 
before the airplane accumulates 12,000 total flight cycles, except 
as required by paragraph (m) of this AD, in accordance with Boeing 
Alert Service Bulletin 767-57A0079, dated June 20, 2002; or the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0079, Revision 2, dated March 23, 2012. As of the effective date 
of this AD, only Boeing Alert Service Bulletin 767-57A0079, Revision 
2, dated March 23, 2012, may be used for the inspection.

(h) Retained Follow-On/Corrective Actions, With Revised Service 
Information

    This paragraph restates the requirements of paragraph (b) of AD 
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with 
revised service information. Following the initial inspections 
required by paragraph (g) of this AD, perform applicable follow-on 
and corrective actions at the times specified in Figure 1 of Boeing 
Service Bulletin 767-57A0076, Revision 1, dated March 29, 2001 (for 
Model 767-200, -300, and -300F series airplanes); or Boeing Alert 
Service Bulletin 767-57A0079, dated June 20, 2002 (for Model 767-
400ER series airplanes); until the initial inspection required by 
paragraph (n) of this AD is accomplished, and repeat thereafter at 
the applicable times specified in paragraph (n) of this AD. Do the 
follow-on and corrective actions (including repetitive inspections 
and replacement of the fittings with new fittings) in accordance 
with Part 1 or Part 2 of Boeing Service Bulletin 767-57A0076, 
Revision 1, dated March 29, 2001; or Boeing Alert Service Bulletin 
767-57A0079, dated June 20, 2002; or in accordance with the 
Accomplishment Instructions of the service information identified in 
paragraph (h)(1) or (h)(2) of this AD; except as required by 
paragraph (i)(2) of this AD. For Model 767-200, -300, and -300F 
series airplanes: If the fitting has the tool runout, and no 
cracking or fracture is found during the inspection, this AD 
requires no further action for that hinge fitting. As of the 
effective date of this AD, for the actions required by this 
paragraph, only the service information identified in paragraph 
(h)(1) or (h)(2) of this AD, as applicable, may be used.
    (1) Boeing Service Bulletin 767-57A0076, Revision 3, dated April 
4, 2012 (for Model 767-200, -300, and -300F series airplanes).
    (2) Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated 
March 23, 2012 (for Model 767-400ER series airplanes).

(i) Retained Exceptions to Service Bulletin Procedures, Without the 
Reporting Requirement and With Revised Service Information

    This paragraph restates the requirements of paragraphs (c) and 
(d) of AD 2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 
2003), without the reporting requirement and with revised service 
information. The following exceptions specified in paragraphs (i)(1) 
and (i)(2) of this AD apply.
    (1) Where the terminating action in Part 3 of Boeing Service 
Bulletin 767-57A0076, Revision 1, dated March 29, 2001, and Revision 
3, dated April 4, 2012; and Boeing Alert Service Bulletin 767-
57A0079, dated June 20, 2002, and Revision 2, dated March 23, 2012; 
as applicable; is specified as corrective action, this AD requires 
that the terminating action, if required, be accomplished before 
further flight.
    (2) Boeing Service Bulletin 767-57A0076, Revision 1, dated March 
29, 2001; and Boeing Alert Service Bulletin 767-57A0076, Revision 3, 
dated April 4, 2012; specify to contact Boeing before the 
terminating action is done as corrective action for any cracking or 
fracture found on a Model 767-200, -300, or -300F series airplane 
with the tool runout. However, this AD requires that any such crack 
or fracture on those airplanes be repaired in accordance with Part 3 
of Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 
2001; or the Accomplishment Instructions of Boeing Alert Service 
Bulletin 767-57A0076, Revision 3, dated April 4, 2012. This AD does 
not require a report.

(j) Retained Optional Terminating Action

    This paragraph restates the provisions of paragraph (f) of AD 
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003). Unless 
required to do so by paragraph (h) of this AD, operators may choose 
to accomplish the terminating action (including replacement of the 
fittings with new fittings, and reinstallation of existing upper 
skin access panels and fairing midsections on the trailing edge of 
the main flap) in accordance with Part 3 of the Work Instructions of 
Boeing Service Bulletin 767-57A0076, Revision 1, dated March 29, 
2001; or Boeing Alert Service Bulletin 767-57A0079, dated June 20, 
2002; as applicable; or do the terminating actions specified in 
paragraph (o) of this AD. As of the effective date of this AD, use 
only the terminating action specified in paragraph (o) of this AD. 
Accomplishment of the terminating action terminates the repetitive 
inspection requirements of paragraph (h) of this AD.

(k) Parts Installation Limitations

    As of the effective date of this AD, no person may install on 
any airplane identified

[[Page 61097]]

in paragraph (c) of this AD, a hinge fitting assembly that has part 
number (P/N) 113T2271-13, 113T2271-14, 113T2271-23, 113T2271-24, 
113T2271-29, 113T2271-30, 113T2271-33, 113T2271-34, 113T2271-401, or 
113T2271-402, unless the applicable requirements of this AD have 
been accomplished for that fitting.

(l) Retained Credit for Previous Actions, With Revised Credit 
Provisions

    This paragraph restates the provisions of paragraph (g) of AD 
2003-13-01, Amendment 39-13201 (68 FR 37402, June 24, 2003), with 
revised credit provisions. This paragraph provides credit for 
actions required by paragraphs (g)(1), (h), and (j) of this AD, if 
those actions were performed before July 29, 2003 (the effective 
date of AD 2003-13-01), using Boeing Alert Service Bulletin 767-
57A0076, dated October 26, 2000, which is not incorporated by 
reference in this AD.

(m) New Initial Inspection

    For Model 767-400ER airplanes identified in Boeing Alert Service 
Bulletin 767-57A0079, Revision 2, dated March 23, 2012, on which the 
inspection required in paragraph (g) of this AD has not been done as 
of the effective date of this AD: Before the accumulation of 6,000 
total flight cycles, or within 750 flight cycles after the effective 
date of this AD, whichever occurs later, perform either a detailed 
inspection or a detailed inspection plus an eddy current inspection 
to detect cracks or fractures of the outboard hinge fitting 
assemblies on the trailing edge of the inboard main flap, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 767-57A0079, Revision 2, dated March 23, 2012. 
Accomplishment of this inspection terminates the inspection 
requirement of paragraph (g)(2) of this AD. If any cracking or 
fracture is found, before further flight, replace the fittings in 
accordance with Part 3 of the Work Instructions of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0079, Revision 2, dated March 23, 2012.

(n) New Repetitive Inspections

    Repeat the inspection specified in paragraph (h) or (m) of this 
AD, as applicable, at intervals not to exceed the time specified in 
paragraph (n)(1) or (n)(2) of this AD, as applicable, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 767-57A0076, Revision 3, dated April 4, 2012 (for Model 
767-200, -300, and -300F series airplanes); or Boeing Alert Service 
Bulletin 767-57A0079, Revision 2, dated March 23, 2012 (for Model 
767-400ER series airplanes); until the actions specified in 
paragraph (o) of this AD are done.
    (1) If the most recent inspection was a detailed inspection: Do 
the next inspection within 300 flight cycles after doing the 
detailed inspection, and continue to repeat the inspection(s) 
thereafter at the time specified in paragraph (n) of this AD.
    (2) If the most recent inspections were a detailed inspection 
and an eddy current inspection: Do the next inspections at the 
applicable time specified in paragraph (n)(2)(i) or (n)(2)(ii) of 
this AD, and continue to repeat the inspection(s) thereafter at the 
time specified in paragraph (n) of this AD.
    (i) For Model 767-200, -300, and -300F series airplanes: Do the 
next inspection at the applicable time specified in paragraph 
(n)(2)(i)(A) or (n)(2)(i)(B) of this AD.
    (A) If the detailed inspection and eddy current inspection were 
done before the effective date of this AD: Do the next inspection 
within 1,500 flight cycles after doing the detailed and eddy current 
inspections.
    (B) If the detailed inspection and eddy current inspection were 
done on or after the effective date of this AD: Do the next 
inspection within 750 flight cycles after doing the detailed and 
eddy current inspection.
    (ii) For Model 767-400ER series airplanes: Do the next 
inspection within 750 flight cycles after doing the detailed 
inspection and eddy current inspection.

(o) New Optional Terminating Action

    Replacement of the inboard main flap outboard hinge fittings in 
accordance with step 4 of Part 3 of the Work Instructions of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0079, Revision 2, dated March 23, 2012 (for Model 767-400ER 
series airplanes); or step 4 of Part 3 of the Work Instructions of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-57A0076, Revision 3, dated April 4, 2012 (for Model 767-200, -
300, and -300F series airplanes); terminates the repetitive 
inspections required by paragraphs (h) and (n) of this AD.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Alert Service Bulletin 
767-57A0079, Revision 1, dated May 6, 2010, which is not 
incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraphs (h), (n), and (o) of this AD, if those actions were 
performed before the effective date of this AD using the service 
information identified in paragraph (p)(2)(i), (p)(2)(ii), 
(p)(2)(iii), or (p)(2)(iv) of this AD.
    (i) Boeing Alert Service Bulletin 767-57A0076, Revision 1, dated 
March 29, 2001, which was incorporated by reference in AD 2003-13-
01, Amendment 39-13201 (68 FR 37402, June 24, 2003), and continues 
to be incorporated by reference in this AD.
    (ii) Boeing Alert Service Bulletin 767-57A0076, Revision 2, 
dated November 22, 2006, which is not incorporated by reference in 
this AD.
    (iii) Boeing Alert Service Bulletin 767-57A0079, dated June 20, 
2002, which was incorporated by reference in AD 2003-13-01, 
Amendment 39-13201 (68 FR 37402, June 24, 2003), and continues to be 
incorporated by reference in this AD.
    (iv) Boeing Alert Service Bulletin 767-57A0079, Revision 1, 
dated May 6, 2010, which is not incorporated by reference in this 
AD.
    (3) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraph (p)(3)(i) or (p)(3)(ii) of this AD.
    (i) Boeing Alert Service Bulletin 767-57A0076, Revision 2, dated 
November 22, 2006, which is not incorporated by reference in this 
AD.
    (ii) Boeing Alert Service Bulletin 767-57A0079, Revision 1, 
dated May 6, 2010, which is not incorporated by reference in this 
AD.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (r)(1) of this AD. 
Information may be emailed to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 2003-13-01, 
Amendment 39-13201 (68 FR 37402, June 24, 2003), are approved as 
AMOCs for the corresponding provisions of paragraphs (g), (h), (i), 
and (j) of this AD.

(r) Related Information

    (1) For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office ACO, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6447; fax: 425-917-6590; email: 
wayne.lockett@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(5) and (s)(6) of this AD.

(s) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 13, 2015.
    (i) Boeing Alert Service Bulletin 767-57A0079, Revision 2, dated 
March 23, 2012.

[[Page 61098]]

    (ii) Boeing Alert Service Bulletin 767-57A0076, Revision 3, 
dated April 4, 2012.
    (4) The following service information was approved for IBR on 
July 29, 2003 (68 FR 37402, June 24, 2003).
    (i) Boeing Alert Service Bulletin 767-57A0079, dated June 20, 
2002.
    (ii) Boeing Service Bulletin 767-57A0076, Revision 1, dated 
March 29, 2001.
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-25490 Filed 10-8-15; 8:45 am]
 BILLING CODE 4910-13-P


