
[Federal Register Volume 77, Number 160 (Friday, August 17, 2012)]
[Rules and Regulations]
[Pages 49708-49710]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-19819]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0490; Directorate Identifier 2012-NM-066-AD; 
Amendment 39-17159; AD 2012-16-12]
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 adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 707 airplanes, and Model 720 and 720B series 
airplanes. This AD was prompted by reports of cracking of the midspar 
fittings, and of the engine and nacelle strut separating from the 
airplane. This AD requires performing a detailed inspection of the 
midspar fittings of the nacelle strut to confirm that the correct part 
number is installed, and installing the correct part number if 
necessary; performing repetitive high frequency eddy current (HFEC) 
inspections of the midspar fittings of the nacelle strut for cracks, 
and repair if necessary; and performing repetitive general visual 
inspections of the nacelle struts to verify that the nacelle strut has 
not drooped below its normal position, applying the droop stripe to the 
nacelle strut and sailboat fairing if necessary, and performing repair 
if necessary. We are issuing this AD to detect and correct cracking of 
the midspar fitting, which could result in separation of the nacelle 
strut and engine from the airplane while in flight, and consequent loss 
of controllability of the airplane.

DATES: This AD is effective September 21, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of September 21, 
2012.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, 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 Document 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: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6577; 
fax: (425) 917-6590; email: Berhane.Alazar@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on May 30, 2012 (77 FR 
31762). That NPRM proposed to require performing a detailed inspection 
of the midspar fittings of the nacelle strut to confirm that the 
correct part number is installed, and installing the correct part 
number if necessary; performing repetitive HFEC inspections of the 
midspar fittings of the nacelle strut for cracks, and repair if 
necessary; and performing repetitive general visual inspections of the 
nacelle struts to verify that the nacelle strut has not drooped below 
its normal position, applying the droop stripe to the nacelle strut and 
sailboat fairing if necessary, and performing repair if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. Boeing and the 
National Transportation Safety Board support the NPRM.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Costs of Compliance

    We estimate that this AD affects 11 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
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                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per product       operators
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Detailed inspection, repetitive  23 work-hours x $85 per              $0   $1,955, per         $21,505, per
 HFEC inspections, and            hour = $1,955, per                        inspection.         inspection.
 repetitive general visual        inspection.
 inspections of the midspar
 fittings of the nacelle strut.
----------------------------------------------------------------------------------------------------------------

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

[[Page 49709]]



                                               On-Condition Costs
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                                                                                                     Cost per
               Action                          Labor cost                    Parts cost              product
----------------------------------------------------------------------------------------------------------------
Install the correct part number.....  130 work-hours x $85 per      $7,867 x 4 = $31,468.......         $42,518
                                       hour = $11,050.
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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

    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 adding the following new airworthiness 
directive (AD):

2012-16-12 The Boeing Company: Amendment 39-17159; Docket No. FAA-
2012-0490; Directorate Identifier 2012-NM-066-AD.

(a) Effective Date

    This AD is effective September 21, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 707-100 long 
body, -200, -100B long body, and -100B short body series airplanes; 
Model 707-300, -300B, -300C, and -400 series airplanes; and Model 
720 and 720B series airplanes; certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 54, Nacelles/Pylons.

(e) Unsafe Condition

    This AD was prompted by reports of cracking of the midspar 
fittings and of the engine and nacelle strut separating from the 
airplane. We are issuing this AD to detect and correct cracking of 
the midspar fitting, which could result in separation of the nacelle 
strut and engine from the airplane while in flight, and consequent 
loss of controllability of the airplane.

(f) Compliance

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

(g) Detailed Inspection

    Within 120 days after the effective date of this AD: Do a 
detailed inspection of the midspar fittings of engine numbers 2 and 
3 nacelle struts to confirm that the correct part number is 
installed, in accordance with the Accomplishment Instructions of 
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012 
(which is not incorporated by reference in this AD). If any 
incorrect part number is found: Before further flight, install the 
correct part number, in accordance with the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012.

    Note 1 to paragraph (g) of this AD: Boeing 707 Alert Service 
Bulletin A3537, dated January 30, 2012, refers to Boeing 707/720 
Service Bulletin 3183, Revision 5, dated September 16, 1993 (which 
is not incorporated by reference in this AD), as an additional 
source of guidance for high frequency eddy current (HFEC) 
inspections of the midspar fittings of engine numbers 2 and 3 
nacelle struts for cracks.

(h) HFEC Inspection

    At the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012, except as provided in paragraph (j) of this AD: Do 
an HFEC inspection of the midspar fittings of engine numbers 2 and 3 
nacelle struts for cracks, in accordance with the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012, except as provided by paragraph (k) of this AD. If 
any crack is found, before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(m) of this AD. Thereafter, repeat the inspection at the applicable 
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 707 
Alert Service Bulletin A3537, dated January 30, 2012.

(i) General Visual Inspection of the Nacelle Struts of Engine Numbers 
1, 2, 3, and 4

    At the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012, except as provided in paragraph (j) of this AD: Do 
a general visual inspection of the nacelle struts of engine numbers 
1, 2, 3, and 4 to verify that the nacelle strut has not drooped 
below its normal position, in accordance with the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012. Thereafter, repeat the inspection at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Boeing 707 Alert Service Bulletin A3537, dated January 30, 2012.
    (1) If any nacelle strut has drooped below its normal position: 
Before further flight, repair using a method approved in accordance 
with the procedures specified in paragraph (m) of this AD.
    (2) If any nacelle strut has not drooped below its normal 
position, and no droop stripe specified in Boeing 707/720 Service 
Bulletin 3377, dated November 21, 1979 (which is not incorporated by 
reference in this AD) has been applied: At the applicable times in 
paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin 
A3537, dated January 30, 2012, except as provided

[[Page 49710]]

in paragraph (j) of this AD: Apply the droop stripe to the nacelle 
strut and sailboat fairing, on each side of engine numbers 1, 2, 3, 
and 4 nacelle struts, in accordance with the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3537, dated 
January 30, 2012.

(j) Exception to the Compliance Times

    Where Boeing 707 Alert Service Bulletin A3537, dated January 30, 
2012, specifies a compliance time based on ``the original issue date 
of this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.

(k) Exception to the Service Information

    Where Boeing 707 Alert Service Bulletin A3537, dated January 30, 
2012, refers to ``Manual 707, 720 NDT Part 6, 51-00-00 Figure 24 as 
an accepted procedure'' for the HFEC inspection, this AD requires 
that the inspection be done in accordance with Figure 24, Steel Part 
Surface Inspection (Impedance Plane Display), Subject 51-00-00, 
Structural-General, of Part 6, Eddy Current, of the Boeing 707/720 
Nondestructive Test Manual, Document D6-48023, Revision 120, dated 
March 15, 2012.

(l) Credit for Previous Actions

    This paragraph provides credit for the installation of the 
engine droop lines required by paragraph (i) of this AD, if those 
actions were performed before the effective date of this AD using 
Boeing 707/720 Service Bulletin 3377, dated November 21, 1979 (which 
is not incorporated by reference in this AD).

(m) 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 the Related Information 
section 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.

(n) Related Information

    (1) For more information about this AD, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: (425) 917-6577; fax: (425) 917-6590; email: 
Berhane.Alazar@faa.gov.
    (2) For service information identified in this AD, that is not 
incorporated by reference in this AD, contact Boeing Commercial 
Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 
2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

(o) 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.
    (i) Boeing 707 Alert Service Bulletin A3537, dated January 30, 
2012.
    (ii) Figure 24, Steel Part Surface Inspection (Impedance Plane 
Display), Subject 51-00-00, Structural--General, of Part 6, Eddy 
Current, of the Boeing 707/720 Nondestructive Test Manual, Document 
D6-48023, Revision 120, dated March 15, 2012. The revision level of 
this document is identified on only the manual revision Transmittal 
Sheet.
    (3) For The Boeing Company service information identified in 
this AD, contact Boeing Commercial Airplanes, Attention: Data & 
Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 
98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; 
Internet https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) 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/index.html.

    Issued in Renton, Washington, on August 3, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-19819 Filed 8-16-12; 8:45 am]
BILLING CODE 4910-13-P


