

[Federal Register: January 7, 2008 (Volume 73, Number 4)]
[Rules and Regulations]               
[Page 1052-1055]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ja08-5]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0411; Directorate Identifier 2007-NM-291-AD; 
Amendment 39-15326; AD 2004-07-22 R1]
RIN 2120-AA64

 
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
that applies to all Boeing Model 747 series airplanes. That AD 
currently requires that the FAA-approved maintenance inspection program 
be revised to include inspections that will give no less than the 
required damage tolerance rating for each structural significant item, 
and repair of cracked structure. We issued that AD to ensure the 
continued structural integrity of the entire fleet of Model 747 series 
airplanes. This new AD clarifies the applicability of the existing AD 
by specifying which Boeing Model 747 airplanes are affected by this AD 
because we have determined that certain new variants that have not yet 
been certified will not be subject to the requirements of this AD. This 
AD results from a report of incidents involving fatigue cracking in 
transport category airplanes that are approaching or have exceeded 
their design service objective. We are issuing this AD to ensure the 
continued structural integrity of all Boeing Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes.

DATES: Effective January 22, 2008.
    The incorporation by reference of Boeing Document D6-35022, 
``Supplemental Structural Inspection Document (SSID) for Model 747 
Airplanes,'' Revision G, dated December 2000, was approved previously 
by the Director of the Federal Register as of May 12, 2004 (69 FR 
18250, April 7, 2004).
    The incorporation by reference of Boeing Document No. D6-35022, 
Volumes 1 and 2, ``Supplemental Structural Inspection Document (SSID) 
for Model 747 Airplanes,'' Revision E, dated June 17, 1993, was 
approved previously by the Director of the Federal Register as of 
September 12, 1994 (59 FR 41233, August 11, 1994).
    The incorporation by reference of Boeing Document No. D6-35655, 
``Supplemental Structural Inspection Document for 747-100SR,'' dated 
April 2, 1986, was approved previously by the Director of the Federal 
Register as of August 10, 1994 (59 FR 37933, July 26, 1994).
    We must receive comments on this AD by March 7, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov.
 Follow the instructions for submitting comments.

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.

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 street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    On March 24, 2004, we issued AD 2004-07-22, amendment 39-13566 (69 
FR 18250, April 7, 2004). A correction of that AD was published in the 
Federal Register on May 3, 2004 (69 FR 24063). AD 2004-07-22 applies to 
all Boeing Model 747 series airplanes. That AD requires that the FAA-
approved maintenance inspection program be revised to include 
inspections that will give no less than the required damage tolerance 
rating for each structural significant item, and repair of cracked 
structure. That AD resulted from a report of incidents involving 
fatigue cracking in transport category airplanes that are approaching 
or have exceeded their design service objective. We issued that AD to 
ensure the continued structural integrity of the entire fleet of Model 
747 series airplanes.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-07-22, Boeing has announced the production 
of additional Model 747 variants. Although they have not yet been 
certified, the new variants (Model 747-8 and -8F series airplanes) have 
a certification basis that will alleviate the safety issues addressed 
by AD 2004-07-22. All of the supplemental structural inspections 
required by AD 2004-07-22 will be included in the Airworthiness 
Limitations Section of the Boeing 747-8/8F Maintenance Planning Data 
Document.
    Because AD 2004-07-22 currently applies to ``all Boeing Model 747 
series airplanes,'' these additional Model 747

[[Page 1053]]

variants will be required to do the actions mandated by that AD, once 
they are certified. Therefore, we must clarify the applicability to 
specify only the airplanes that are affected by this AD.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. For this reason, we 
are issuing this AD to revise AD 2004-07-22. This new AD retains the 
requirements of the existing AD. This AD also clarifies the 
applicability of the existing AD.

Change to Existing AD

    Since we issued AD 2004-07-22, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this AD, as listed in the 
following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding  requirement in
       Requirement in AD 2004-07-22               AD 2004-07-22 R1
------------------------------------------------------------------------
Paragraph (a)............................  Paragraph (f).
Paragraph (b)............................  Paragraph (g).
Paragraph (c)............................  Paragraph (h).
Paragraph (d)............................  Paragraph (i).
(This paragraph was mis-lettered as (a)
 in the Federal Register.).
Paragraph (e)............................  Paragraph (j).
Paragraph (f)............................  Paragraph (k).
------------------------------------------------------------------------

    We have also removed Note 1 of AD 2004-07-22 from this AD. The 
information in that note is now included in the Federal Aviation 
Regulations (14 CFR part 39) and it is not necessary to include it in 
this AD. We have re-numbered the notes in AD 2004-07-22 R1 accordingly.

Costs of Compliance

    We estimate that this AD affects about 165 airplanes of U.S. 
registry. The requirements of this AD add no additional economic 
burden. The current costs for this AD are repeated for the convenience 
of affected operators, as follows:
    We estimate that the actions required by AD 2004-07-22 and retained 
in this AD take up to 6,825 work-hours per product. The average labor 
rate is $80 per work hour. Based on these figures, we estimate the cost 
of this AD to U.S. operators to be up to $90,090,000 or up to $546,000 
per product.
    The number of work hours, as indicated above, is presented as if 
the accomplishment of the actions required by AD 2004-07-22 and 
retained in this AD are to be conducted as ``stand alone'' actions. 
However, in actual practice, these actions for the most part will be 
accomplished coincidentally or in combination with normally scheduled 
airplane inspections and other maintenance program tasks. Therefore, 
the actual number of necessary additional work hours will be minimal in 
many instances. Additionally, any costs associated with special 
airplane scheduling will be minimal.

FAA's Determination of the Effective Date

    No airplane variant that we had previously excluded from the 
applicability of this AD is currently on the U.S. Register. Therefore, 
providing notice and opportunity for public comment is unnecessary 
before this AD is issued, and this AD may be made effective in less 
than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2008-0411; Directorate Identifier 2007-NM-291-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We 

will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13566 (69 FR 18250, April 7, 2004), corrected at 
69 FR 24063, May 3, 2004, and adding the following new airworthiness 
directive (AD):

2004-07-22 R1 Boeing: Amendment 39-15326. Docket No. FAA-2008-0411; 
Directorate Identifier 2007-NM-291-AD.

Effective Date

    (a) This AD becomes effective January 22, 2008.

[[Page 1054]]

Affected ADs

    (b) This AD revises AD 2004-07-22.

Applicability

    (c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes, certificated in any 
category.

Unsafe Condition

    (d) This AD results from a report of incidents involving fatigue 
cracking in transport category airplanes that are approaching or 
have exceeded their design service objective. We are issuing this AD 
to ensure the continued structural integrity of all Boeing Model 
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-
300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

    Note 1: Where there are differences between this AD and the 
supplemental structural inspection document (SSID) specified in this 
AD, the AD prevails.

Requirements of AD 2004-07-22

Inspection Program

    (f) For Model 747-100SR series airplanes having line numbers 
346, 351, 420, 426, 427, and 601: Within 1 year after August 10, 
1994 (the effective date of AD 94-15-12, amendment 39-8983, which 
was superseded by AD 2004-07-22), incorporate a revision into the 
FAA-approved maintenance inspection program that provides no less 
than the required damage tolerance rating (DTR) for each structural 
significant item (SSI) listed in Boeing Document No. D6-35655, 
``Supplemental Structural Inspection Document (SSID) for 747-
100SR,'' dated April 2, 1986. The revision to the maintenance 
program must include and be implemented per the procedures specified 
in Sections 5.0 and 6.0 of the SSID D6-35655. Revision to the 
maintenance program shall be per the SSID D6-35655, dated April 2, 
1986, until Revision G of the SSID D6-35022 is incorporated into the 
FAA-approved maintenance or inspection program per the requirements 
of paragraph (h) of this AD.

    Note 2: For the purposes of this AD, an SSI is defined as a 
principal structural element (PSE). A PSE is a structural element 
that contributes significantly to the carrying of flight, ground, or 
pressurization loads, and whose integrity is essential in 
maintaining the overall structural integrity of the airplane.

    (g) For airplanes listed in Boeing Document No. D6-35022, 
Volumes 1 and 2, ``Supplemental Structural Inspection Document 
(SSID) for Model 747 Airplanes,'' Revision E, dated June 17, 1993; 
and manufacturer's line numbers 42, 174, 221, 231, 234, 239, 242, 
and 254: Within 12 months after September 12, 1994 (the effective 
date of AD 94-15-18, amendment 39-8989, which was superseded by AD 
2004-07-22), incorporate a revision into the FAA-approved 
maintenance inspection program that provides no less than the 
required DTR for each SSI listed in Boeing Document No. D6-35022, 
Volumes 1 and 2, ``Supplemental Structural Inspection Document 
(SSID) for Model 747 Airplanes,'' Revision E, dated June 17, 1993. 
Revision F, dated May 1996, is acceptable for compliance with this 
paragraph. (The required DTR value for each SSI is listed in the 
document.) The revision to the maintenance program shall include 
Sections 5.0 and 6.0 of the SSID D6-35022 and shall be implemented 
per the procedures contained in those sections. Revision to the 
maintenance program shall be per Revision E or F of SSID D6-35022, 
until Revision G of the SSID D6-35022 is incorporated into the FAA-
approved maintenance or inspection program per the requirements of 
paragraph (h) of this AD.
    (h) For all Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 
747SP series airplanes: Prior to reaching either of the thresholds 
specified in paragraph (i)(1)(i) or (i)(2)(i) of this AD, or within 
12 months after May 12, 2004 (the effective date of AD 2004-07-22), 
whichever occurs later, incorporate a revision into the FAA-approved 
maintenance or inspection program that provides no less than the 
required DTR for each SSI listed in Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document,'' Revision G, dated 
December 2000 (hereinafter referred to as ``Revision G''). (The 
required DTR value for each SSI is listed in Revision G.) The 
revision to the maintenance or inspection program shall include and 
shall be implemented per the procedures in Section 5.0, ``DTR System 
Application'' and Section 6.0, ``SSI Discrepancy Reporting'' of 
Revision G, excluding paragraphs 5.1.2; 5.1.6, item 5; 5.1.8; 5.2; 
5.2.1; 5.2.2; 5.2.3; and 5.2.4 of Revision G. Under the provisions 
of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501, et seq.), 
the Office of Management and Budget (OMB) has approved the 
information collection requirements (Section 6.0, ``SSI Discrepancy 
Reporting'') contained in this AD and has assigned OMB Control 
Number 2120-0056. Upon incorporation of Revision G required by this 
paragraph, the revision required by either paragraph (f) or (g) of 
this AD, as applicable, may be removed.

    Note 3: Operators should note that, although paragraph 5.2 is 
referenced in paragraph 5.1.11 of Revision G, paragraph 5.2 is 
excluded as a method of compliance with the requirements of this AD.

Initial Inspection

    (i) For all Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 
747SP series airplanes: Perform an inspection to detect cracks of 
all structure identified in Revision G of SSID D6-35022 at the time 
specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as 
applicable.
    (1) For wing structure: At the times specified in paragraph 
(i)(1)(i) or (i)(1)(ii) of this AD, whichever occurs later.
    (i) Prior to the accumulation of 20,000 total flight cycles or 
100,000 total flight hours, whichever comes first. Or,
    (ii) Within 1,000 flight cycles measured from 12 months after 
May 12, 2004.
    (2) For all other structure: At the times specified in paragraph 
(i)(2)(i) or (i)(2)(ii) of this AD, whichever occurs later.
    (i) Prior to the accumulation of 20,000 total flight cycles, or
    (ii) Within 1,000 flight cycles measured from 12 months after 
May 12, 2004.
    (3) For any portion of an SSI that has been replaced with new 
structure: At the later of the times specified in paragraph 
(i)(3)(i) or (i)(3)(ii) of this AD.
    (i) At the times specified in either paragraph (i)(1) or (i)(2) 
of this AD, as applicable, or
    (ii) Within 10,000 flight cycles after the replacement of the 
part with a new part.

    Note 4: Notwithstanding the provisions of paragraphs 5.1.2, 
5.1.6, item 5, 5.2, 5.2.1, 5.2.2, 5.2.3, and 5.2.4 of the General 
Instructions of Revision G, which would permit operators to perform 
fleet and rotational sampling inspections to perform inspections on 
less than whole airplane fleet sizes and to perform inspections on 
substitute airplanes, this AD requires that all airplanes that 
exceed the threshold be inspected per Revision G. Although paragraph 
5.1.8 of Revision G allows provisions for touch-and-go training 
flights, fleet averaging, and 10% escalations of flight cycles to 
achieve the required DTR, this AD does not allow for those 
provisions.


    Note 5: Once the initial inspection has been performed, 
operators are required to perform repetitive inspections at the 
intervals specified in Revision G in order to remain in compliance 
with their maintenance or inspection programs, as revised per 
paragraph (h) of this AD.

Repair

    (j) Cracked structure found during any inspection required by 
this AD shall be repaired, prior to further flight, in accordance 
with an FAA-approved method.

Inspection Program for Transferred Airplanes

    (k) Before any airplane that is subject to this AD and that has 
exceeded the applicable compliance times specified in paragraph (i) 
of this AD can be added to an air carrier's operations 
specifications, a program for the accomplishment of the inspections 
required by this AD must be established per paragraph (k)(1) or 
(k)(2) of this AD, as applicable.
    (1) For airplanes that have been inspected per this AD, the 
inspection of each SSI must be accomplished by the new operator per 
the previous operator's schedule and inspection method, or the new 
operator's schedule and inspection method, at whichever time would 
result in the earlier accomplishment for that SSI inspection. The 
compliance time for accomplishment of this inspection must be 
measured from the last inspection accomplished by the previous 
operator. After each inspection has been performed once, each 
subsequent inspection must be performed per the new operator's 
schedule and inspection method.
    (2) For airplanes that have not been inspected per this AD, the 
inspection of each SSI required by this AD must be accomplished 
either prior to adding the

[[Page 1055]]

airplane to the air carrier's operations specification, or per a 
schedule and an inspection method approved by the Manager, Seattle 
Aircraft Certification Office (ACO). After each inspection has been 
performed once, each subsequent inspection must be performed per the 
new operator's schedule.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6437; fax (425) 
917-6590; has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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 an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who 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 94-15-12, 
are approved as alternative methods of compliance for the 
requirements of paragraphs (f) and (j) of this AD.
    (5) AMOCs approved previously in accordance with AD 94-15-18, 
are approved as alternative methods of compliance for the 
requirements of paragraphs (g) and (j) of this AD.
    (6) AMOCs approved previously in accordance with AD 2004-07-22, 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (m) You must use Boeing Document No. D6-35655, ``Supplemental 
Structural Inspection Document for 747-100SR,'' dated April 2, 1986; 
Boeing Document No. D6-35022, Volumes 1 and 2, ``Supplemental 
Structural Inspection Document (SSID) for Model 747 Airplanes,'' 
Revision E, dated June 17, 1993; and Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document (SSID) for Model 747 
Airplanes,'' Revision G, dated December 2000; as applicable; to 
perform the actions that are required by this AD, unless the AD 
specifies otherwise.
    (1) The incorporation by reference of Boeing Document D6-35022, 
``Supplemental Structural Inspection Document (SSID) for Model 747 
Airplanes,'' Revision G, dated December 2000, was approved 
previously by the Director of the Federal Register as of May 12, 
2004 (69 FR 18250, April 7, 2004).
    (2) The incorporation by reference of Boeing Document No. D6-
35022, Volumes 1 and 2, ``Supplemental Structural Inspection 
Document (SSID) for Model 747 Airplanes,'' Revision E, dated June 
17, 1993, was approved previously by the Director of the Federal 
Register as of September 12, 1994 (59 FR 41233, August 11, 1994).
    (3) The incorporation by reference of Boeing Document No. D6-
35655, ``Supplemental Structural Inspection Document for 747-
100SR,'' dated April 2, 1986, was approved previously by the 
Director of the Federal Register as of August 10, 1994 (59 FR 37933, 
July 26, 1994).
    (4) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98057-3356; or 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 December 26, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-25614 Filed 1-4-08; 8:45 am]

BILLING CODE 4910-13-P
