Airworthiness Directives; The Boeing Company Airplanes, 65616-65618 [2015-26979]

Download as PDF 65616 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations (i) Related Information For more information about this AD, contact Katheryn Malatek, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: katheryn.malatek@faa.gov. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on October 21, 2015. Colleen M. D’Alessandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–27184 Filed 10–26–15; 8:45 am] BILLING CODE 4910–13–P 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 http:// www.regulations.govby searching for and locating Docket No. FAA–2015– 0498. ADDRESSES: Examining the AD Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0498; Directorate Identifier 2014–NM–152–AD; Amendment 39–18305; AD 2015–22–01] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2007–16– 08, which applied to all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes. AD 2007–16–08 required repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. This new AD continues to require repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary, and expands the inspection area. This AD was prompted by reports of cracks found at the forward and aft inner chord strap and angles on the station 800 frame on the left-side and right-side main entry doors. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. DATES: This AD is effective December 1, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 1, 2015. tkelley on DSK3SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 16:49 Oct 26, 2015 Jkt 238001 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0498; 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: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6432; fax: 425– 917–6590; email: bill.ashforth@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007). AD 2007–16–08 applied to all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes. The NPRM published in the Federal Register on March 30, 2015 (80 FR 16606). The NPRM was prompted by reports of cracks found at the forward and aft inner chord strap and angles on the station 800 frame on the left-side and right-side main entry doors. The NPRM proposed to continue to require repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary, and expand the inspection PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 area. We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 16606, March 30, 2015) and the FAA’s response to each comment. Support for the NPRM (80 FR 16606, March 30, 2015) Boeing stated that it concurred with the contents of the NPRM (80 FR 16606, March 30, 2015). Statement Regarding the NPRM (80 FR 16606, March 30, 2015) United Airlines stated that it has reviewed the NPRM (80 FR 16606, March 30, 2015), and has no comment to submit. Request To Clarify Inspection Requirements UPS requested that we add an additional statement to paragraph (i) of the proposed AD (‘‘Exception to the Service Information,’’) to clarify that the removal of fasteners is not required for performing the surface high-frequency eddy current (HFEC) inspections specified by paragraph (g) of the proposed AD (80 FR 16606, March 30, 2015). UPS stated that by adding the clarification that the removal of fasteners is not required, significant time and materials would be saved by operators when accomplishing this inspection and prevent unnecessary alternative method of compliance (AMOC) requests. UPS explained that Boeing agreed in a response to a service request that fastener removal is not required for performing surface HFEC inspections. We agree because the clarification will reduce costs while ensuring the same level of safety. We have added the following sentence to paragraph (g) of this AD: ‘‘It is not necessary to remove fasteners while performing the surface HFEC inspections.’’ 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 change described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 16606, March 30, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 16606, March 30, 2015). 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 747–53A2451, Revision 2, dated June 13, 2014. The service information describes procedures for accomplishing repetitive inspections for cracking of the station 800 frame assembly, and repair. This service information is reasonably available 65617 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 AD. Costs of Compliance We estimate that this AD affects 124 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Repetitive inspections Up to 53 work-hours × $85 per hour = $4,505 per inspection cycle. $0 We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. tkelley on DSK3SPTVN1PROD with RULES 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 VerDate Sep<11>2014 16:49 Oct 26, 2015 Jkt 238001 (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 Cost per product Up to $4,505 per inspection cycle. Cost on U.S. operators Up to $558,620 per inspection cycle. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of cracks found on the station 800 frame on the leftside and right-side main entry doors (MED), at the forward and aft inner chord strap and angles, which are outside the inspection area of AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007). We are issuing this AD to detect and correct fatigue cracks that could extend and fully sever the frame, which could result in development of skin cracks that could lead to rapid depressurization of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (c) Applicability (g) Inspections of Station 800 Frame Assembly Between Stringer 14 and Stringer 30 Except as required by paragraph (i) of this AD, at the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014: Do a detailed inspection for cracking in the inner chord strap, angles, and exposed web adjacent to the inner chords, and do surface and open hole high-frequency eddy current (HFEC) inspections for cracking in the inner chord strap and angles of the station 800 frame assembly between stringer 14 and stringer 30, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014. It is not necessary to remove fasteners while performing the surface HFEC inspections. Repeat the inspections at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014. This AD applies to all The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR series airplanes, certificated in any category. (h) Repair of Cracking If any cracking is found during any inspection required by paragraph (g) of this AD, before further flight, repair the cracking using a method approved in accordance with 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007), and adding the following new AD: ■ 2015–22–01 The Boeing Company: Amendment 39–18305; Docket No. FAA–2015–0498; Directorate Identifier 2014–NM–152–AD. (a) Effective Date This AD is effective December 1, 2015. (b) Affected ADs This AD replaces AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007). PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1 65618 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations the procedures specified in paragraph (k) of this AD. (i) Exception to the Service Information (1) Where Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014, specifies a compliance time ‘‘after the Revision 2 date of this service bulletin,’’ this AD requires compliance within the specified time after the effective date of this AD. (2) The Condition column of paragraph 1.E., ‘‘Compliance,’’ of the Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014, refers to total flight cycles ‘‘as of the Revision 2 date of this service bulletin.’’ This AD, however applies to airplanes with the specified total flight cycles or total flight hours as of the effective date of this AD. (j) Credit for Previous Actions This paragraph provides credit for the inspections and repairs of the inner chord strap and angles of the station 800 frame assembly between stringer 14 and stringer 18 required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2451, Revision 1, dated November 10, 2005, which was incorporated by reference in AD 2006–12–12, Amendment 39–14638 (71 FR 33595, June 12, 2006). tkelley on DSK3SPTVN1PROD with RULES (k) 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 (l)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 for AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007), are approved as AMOCs for the corresponding provisions of this AD. (l) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@faa.gov. VerDate Sep<11>2014 16:49 Oct 26, 2015 Jkt 238001 (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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 Alert Service Bulletin 747– 53A2451, Revision 2, dated June 13, 2014. (ii) Reserved. (3) 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. (4) You may view this service information at 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. (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/ibrlocations.html. Issued in Renton, Washington, on October 19, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–26979 Filed 10–26–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–4345; Directorate Identifier 2015–SW–049–AD; Amendment 39–18306; AD 2015–22–02] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are superseding emergency airworthiness directive (AD) No. 2015–16–51 (Emergency AD 2015– 16–51) for Bell Helicopter Textron Canada Limited (Bell) Model 429 helicopters. Emergency AD 2015–16–51 SUMMARY: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 required inspections of each inboard and outboard tail rotor pitch link assembly for axial or radial bearing play, and if there was axial or radial bearing play, removing the tail rotor pitch link and inspecting for wear. Emergency AD 2015–16–51 was prompted by several reports of worn tail rotor pitch link spherical bearings. We are issuing this supersedure to retain the inspection requirements in Emergency AD 2015– 16–51 while revising the applicability and compliance time to clarify that all Bell Model 429 helicopters require recurring inspections regardless of hours time-in-service (TIS) accumulated on the helicopter. These actions are intended to prevent pitch link failure and subsequent loss of control of the helicopter. This AD becomes effective November 12, 2015. We must receive comments on this AD by December 28, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 4345; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the Transport Canada Emergency AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437–2862 or (800) 363–8023; fax (450) 433–0272; or at http:// www.bellcustomer.com/files/. You may review the referenced service information at the FAA, Office of the E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 80, Number 207 (Tuesday, October 27, 2015)]
[Rules and Regulations]
[Pages 65616-65618]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-26979]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0498; Directorate Identifier 2014-NM-152-AD; 
Amendment 39-18305; AD 2015-22-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding Airworthiness Directive (AD) 2007-16-08, 
which applied to all The Boeing Company Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR 
series airplanes. AD 2007-16-08 required repetitive inspections for 
cracking of the station 800 frame assembly, and repair if necessary. 
This new AD continues to require repetitive inspections for cracking of 
the station 800 frame assembly, and repair if necessary, and expands 
the inspection area. This AD was prompted by reports of cracks found at 
the forward and aft inner chord strap and angles on the station 800 
frame on the left-side and right-side main entry doors. We are issuing 
this AD to detect and correct fatigue cracks that could extend and 
fully sever the frame, which could result in development of skin cracks 
that could lead to rapid depressurization of the airplane.

DATES: This AD is effective December 1, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 1, 
2015.

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 http://www.regulations.govby searching for and locating Docket No. FAA-2015-
0498.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0498; 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: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2007-16-08, Amendment 39-15147 (72 FR 44728, 
August 9, 2007). AD 2007-16-08 applied to all The Boeing Company Model 
747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 
747-400D, and 747SR series airplanes. The NPRM published in the Federal 
Register on March 30, 2015 (80 FR 16606). The NPRM was prompted by 
reports of cracks found at the forward and aft inner chord strap and 
angles on the station 800 frame on the left-side and right-side main 
entry doors. The NPRM proposed to continue to require repetitive 
inspections for cracking of the station 800 frame assembly, and repair 
if necessary, and expand the inspection area. We are issuing this AD to 
detect and correct fatigue cracks that could extend and fully sever the 
frame, which could result in development of skin cracks that could lead 
to rapid depressurization of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 16606, March 30, 2015) and the FAA's response to each comment.

Support for the NPRM (80 FR 16606, March 30, 2015)

    Boeing stated that it concurred with the contents of the NPRM (80 
FR 16606, March 30, 2015).

Statement Regarding the NPRM (80 FR 16606, March 30, 2015)

    United Airlines stated that it has reviewed the NPRM (80 FR 16606, 
March 30, 2015), and has no comment to submit.

Request To Clarify Inspection Requirements

    UPS requested that we add an additional statement to paragraph (i) 
of the proposed AD (``Exception to the Service Information,'') to 
clarify that the removal of fasteners is not required for performing 
the surface high-frequency eddy current (HFEC) inspections specified by 
paragraph (g) of the proposed AD (80 FR 16606, March 30, 2015). UPS 
stated that by adding the clarification that the removal of fasteners 
is not required, significant time and materials would be saved by 
operators when accomplishing this inspection and prevent unnecessary 
alternative method of compliance (AMOC) requests. UPS explained that 
Boeing agreed in a response to a service request that fastener removal 
is not required for performing surface HFEC inspections.
    We agree because the clarification will reduce costs while ensuring 
the same level of safety. We have added the following sentence to 
paragraph (g) of this AD: ``It is not necessary to remove fasteners 
while performing the surface HFEC inspections.''

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 change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR

[[Page 65617]]

16606, March 30, 2015) for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 16606, March 30, 2015).
    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 747-53A2451, Revision 2, 
dated June 13, 2014. The service information describes procedures for 
accomplishing repetitive inspections for cracking of the station 800 
frame assembly, and repair. 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 AD.

Costs of Compliance

    We estimate that this AD affects 124 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
----------------------------------------------------------------------------------------------------------------
Repetitive inspections........  Up to 53 work-hours x $85                $0   Up to $4,505 per  Up to $558,620
                                 per hour = $4,505 per                         inspection        per inspection
                                 inspection cycle.                             cycle.            cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in 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 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) 
2007-16-08, Amendment 39-15147 (72 FR 44728, August 9, 2007), and 
adding the following new AD:

2015-22-01 The Boeing Company: Amendment 39-18305; Docket No. FAA-
2015-0498; Directorate Identifier 2014-NM-152-AD.

(a) Effective Date

    This AD is effective December 1, 2015.

(b) Affected ADs

    This AD replaces AD 2007-16-08, Amendment 39-15147 (72 FR 44728, 
August 9, 2007).

(c) Applicability

    This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, 
and 747SR series airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracks found on the station 
800 frame on the left-side and right-side main entry doors (MED), at 
the forward and aft inner chord strap and angles, which are outside 
the inspection area of AD 2007-16-08, Amendment 39-15147 (72 FR 
44728, August 9, 2007). We are issuing this AD to detect and correct 
fatigue cracks that could extend and fully sever the frame, which 
could result in development of skin cracks that could lead to rapid 
depressurization of the airplane.

(f) Compliance

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

(g) Inspections of Station 800 Frame Assembly Between Stringer 14 and 
Stringer 30

    Except as required by paragraph (i) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2451, Revision 2, dated June 
13, 2014: Do a detailed inspection for cracking in the inner chord 
strap, angles, and exposed web adjacent to the inner chords, and do 
surface and open hole high-frequency eddy current (HFEC) inspections 
for cracking in the inner chord strap and angles of the station 800 
frame assembly between stringer 14 and stringer 30, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2451, Revision 2, dated June 13, 2014. It is not 
necessary to remove fasteners while performing the surface HFEC 
inspections. Repeat the inspections at the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2451, Revision 2, dated June 13, 2014.

(h) Repair of Cracking

    If any cracking is found during any inspection required by 
paragraph (g) of this AD, before further flight, repair the cracking 
using a method approved in accordance with

[[Page 65618]]

the procedures specified in paragraph (k) of this AD.

(i) Exception to the Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2451, Revision 2, 
dated June 13, 2014, specifies a compliance time ``after the 
Revision 2 date of this service bulletin,'' this AD requires 
compliance within the specified time after the effective date of 
this AD.
    (2) The Condition column of paragraph 1.E., ``Compliance,'' of 
the Boeing Alert Service Bulletin 747-53A2451, Revision 2, dated 
June 13, 2014, refers to total flight cycles ``as of the Revision 2 
date of this service bulletin.'' This AD, however applies to 
airplanes with the specified total flight cycles or total flight 
hours as of the effective date of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the inspections and repairs 
of the inner chord strap and angles of the station 800 frame 
assembly between stringer 14 and stringer 18 required by paragraphs 
(g) and (h) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2451, Revision 1, dated November 10, 2005, which was incorporated 
by reference in AD 2006-12-12, Amendment 39-14638 (71 FR 33595, June 
12, 2006).

(k) 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 (l)(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 for AD 2007-16-08, Amendment 39-15147 (72 FR 
44728, August 9, 2007), are approved as AMOCs for the corresponding 
provisions of this AD.

(l) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 Alert Service Bulletin 747-53A2451, Revision 2, dated 
June 13, 2014.
    (ii) Reserved.
    (3) 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.
    (4) You may view this service information at 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.
    (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/ibr-locations.html.

    Issued in Renton, Washington, on October 19, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-26979 Filed 10-26-15; 8:45 am]
BILLING CODE 4910-13-P