Airworthiness Directives; The Boeing Company Airplanes, 16606-16608 [2015-07081]

Download as PDF 16606 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules loose, replace the affected bearing with an airworthy bearing. (2) For Model MBB–BK 117 C–2 helicopters: (i) Within the next 100 hours TIS or at the next annual inspection, whichever occurs first, modify the LH and RH guidance units and the lateral control lever by installing bushings and washers to prevent shifting of the bearings in the axial direction as follows: (A) Remove and disassemble the RH guidance unit and install a bushing, P/N L672M1012260, between the lever and the bracket as depicted in Detail B of Figure 4 of Eurocopter Alert Service Bulletin MBB BK117 C–2–67A–010, Revision 3, dated February 8, 2010 (BK117 ASB). Remove and disassemble the LH guidance unit and install a bushing, P/N L672M1012260, between the lever and the bracket as depicted in Detail C of Figure 4 of BK117 ASB. (B) Remove the lateral control lever and install new bushings in accordance with the Accomplishment Instructions, paragraphs 3.C(9)(a) through 3.C(9)(g), of BK 117 ASB. (C) Identify the modified lever assembly by writing ‘‘MBB BK117 C–2–67A–010’’ on the lever with permanent marking pen and protect with a single layer of lacquer (CM 421 or equivalent). (D) Apply corrosion preventive paste (CM 518 or equivalent) on the shank of the screws and install airworthy parts as depicted in Figure 5 of BK117 ASB. (E) At intervals not to exceed 600 hours TIS or 24 months, whichever occurs first, inspect the bearings in the RH guidance unit, LH guidance unit, and lateral control guidance unit for play. If any bearing is loose, replace the affected bearing with an airworthy bearing. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email matthew.fuller@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. tkelley on DSK3SPTVN1PROD with PROPOSALS (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2010–0058, dated March 30, 2010. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA–2015–0674. (i) Subject Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control. VerDate Sep<11>2014 17:11 Mar 27, 2015 Jkt 235001 Issued in Fort Worth, Texas, on March 18, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–06806 Filed 3–27–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0498; Directorate Identifier 2014–NM–152–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2007–16– 08, which 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. AD 2007–16–08 currently requires repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. Since we issued AD 2007–16–08, we have received additional 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. This proposed AD would expand the inspection area. We are proposing 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: We must receive comments on this proposed AD by May 14, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 For service information identified in this proposed 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.gov by 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–0498; Directorate Identifier 2014–NM–152–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed 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 proposed AD. E:\FR\FM\30MRP1.SGM 30MRP1 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules Discussion On July 30, 2007, we issued AD 2007– 16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007), for 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 requires repetitive inspections for cracking of the station 800 frame assembly, and repair if necessary. AD 2007–16–08 resulted from several reports of cracks of the station 800 frame assembly on airplanes that occurred sooner than previously anticipated. We issued AD 2007–16–08 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. Actions Since AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007), Was Issued Since we issued AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007), we received additional reports of cracking 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. These cracks are outside the inspection area of AD 2007–16–08. We have determined that additional inspections are needed. This proposed AD would expand the 16607 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 procedure for inspecting and repairing cracking of the door number 2 forward edge frame assembly at body station 800. Refer to this service information for information on the procedures and compliance times. This service information is reasonably available; see ADDRESSES for ways to access this service information. previously, which, in turn, is referenced in paragraphs (g) and (h) of this proposed AD. This proposed AD would require additional inspections. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ Differences Between This Proposed AD and the Service Information inspection area to include the station 800 frame between stringer 18 and stringer 30. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2007–16–08, Amendment 39–15147 (72 FR 44728, August 9, 2007), this proposed AD would retain certain requirements of AD 2007–16–08. Those requirements are referenced in the service information identified Where Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014, specifies to contact the manufacturer for instructions on how to repair certain conditions, this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 124 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Repetitive inspections. Up to 53 work-hours × $85 per hour = $4,505 per inspection cycle. tkelley on DSK3SPTVN1PROD with PROPOSALS 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 17:11 Mar 27, 2015 Jkt 235001 Cost per product $0 Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Cost on U.S. operators Up to $4,505 per inspection cycle. 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. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. VerDate Sep<11>2014 Parts cost Labor cost Up to $558,620 per inspection cycle (2) Is not a ‘‘significant rule’’ under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: E:\FR\FM\30MRP1.SGM 30MRP1 16608 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2451, Revision 2, dated June 13, 2014. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ (h) Repair of Cracking 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: ■ The Boeing Company: Docket No. FAA– 2015–0498; Directorate Identifier 2014– NM–152–AD. (a) Comments Due Date The FAA must receive comments on this AD action by May 14, 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 Boeing 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 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. tkelley on DSK3SPTVN1PROD with PROPOSALS (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. Repeat the inspections VerDate Sep<11>2014 18:31 Mar 27, 2015 Jkt 235001 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 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. (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) 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. Issued in Renton, Washington, on March 19, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07081 Filed 3–27–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0676; Directorate Identifier 2014–NM–164–AD] RIN 2120–AA64 (k) Alternative Methods of Compliance (AMOCs) Airworthiness Directives; Bombardier, Inc. Airplanes (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 (k)(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. AGENCY: PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD–700–1A10 and BD–700–1A11 airplanes. This proposed AD was prompted by a report of several events where pilots experienced difficulty in lateral control of the airplane after doing a climb through heavy rain conditions and a determination that the cause was water ingress in the aileron control pulley assembly. This proposed AD would require, for certain airplanes, inspecting for correct clearance and rework if necessary, and, for certain other airplanes, installing a cover for the aileron pulley assembly. We are proposing this AD to prevent water ingress in the aileron control pulley assembly, which could freeze in cold conditions and result in reduced control of the airplane. DATES: We must receive comments on this proposed AD by May 14, 2015. SUMMARY: E:\FR\FM\30MRP1.SGM 30MRP1

Agencies

[Federal Register Volume 80, Number 60 (Monday, March 30, 2015)]
[Proposed Rules]
[Pages 16606-16608]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-07081]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0498; Directorate Identifier 2014-NM-152-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2007-16-
08, which 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. AD 2007-16-08 currently requires repetitive 
inspections for cracking of the station 800 frame assembly, and repair 
if necessary. Since we issued AD 2007-16-08, we have received 
additional 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. This proposed AD would expand the inspection 
area. We are proposing 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: We must receive comments on this proposed AD by May 14, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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.gov by 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0498; 
Directorate Identifier 2014-NM-152-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

[[Page 16607]]

Discussion

    On July 30, 2007, we issued AD 2007-16-08, Amendment 39-15147 (72 
FR 44728, August 9, 2007), for 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 requires repetitive 
inspections for cracking of the station 800 frame assembly, and repair 
if necessary. AD 2007-16-08 resulted from several reports of cracks of 
the station 800 frame assembly on airplanes that occurred sooner than 
previously anticipated. We issued AD 2007-16-08 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.

Actions Since AD 2007-16-08, Amendment 39-15147 (72 FR 44728, August 9, 
2007), Was Issued

    Since we issued AD 2007-16-08, Amendment 39-15147 (72 FR 44728, 
August 9, 2007), we received additional reports of cracking 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. These cracks 
are outside the inspection area of AD 2007-16-08. We have determined 
that additional inspections are needed. This proposed AD would expand 
the inspection area to include the station 800 frame between stringer 
18 and stringer 30.

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 procedure for 
inspecting and repairing cracking of the door number 2 forward edge 
frame assembly at body station 800. Refer to this service information 
for information on the procedures and compliance times. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2007-16-08, Amendment 39-15147 (72 FR 44728, August 
9, 2007), this proposed AD would retain certain requirements of AD 
2007-16-08. Those requirements are referenced in the service 
information identified previously, which, in turn, is referenced in 
paragraphs (g) and (h) of this proposed AD. This proposed AD would 
require additional inspections. This proposed AD would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
this Proposed AD and the Service Information.''

Differences Between This Proposed AD and the Service Information

    Where Boeing Alert Service Bulletin 747-53A2451, Revision 2, dated 
June 13, 2014, specifies to contact the manufacturer for instructions 
on how to repair certain conditions, this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 124 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Repetitive inspections.........  Up to 53 work-hours x                $0  Up to $4,505 per    Up to $558,620 per
                                  $85 per hour = $4,505                    inspection cycle.   inspection cycle
                                  per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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),
    (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.

The Proposed Amendment

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

[[Page 16608]]

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:

The Boeing Company: Docket No. FAA-2015-0498; Directorate Identifier 
2014-NM-152-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 14, 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 Boeing 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. 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 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.

(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 (k)(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) 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.

    Issued in Renton, Washington, on March 19, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07081 Filed 3-27-15; 8:45 am]
BILLING CODE 4910-13-P