80 FR 16606 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 60 (March 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 60 (March 30, 2015)
| Page Range | 16606-16608 | |
| FR Document | 2015-07081 |
[Federal Register Volume 80, Number 60 (Monday, March 30, 2015)] [Proposed Rules] [Pages 16606-16608] From the Federal Register Online [www.thefederalregister.org] [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: [email protected]. 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: [email protected]. (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: [email protected]. (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
![16606 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules
loose, replace the affected bearing with an Issued in Fort Worth, Texas, on March 18, For service information identified in
airworthy bearing. 2015. this proposed AD, contact Boeing
(2) For Model MBB–BK 117 C–2 Lance T. Gant, Commercial Airplanes, Attention: Data
helicopters: Acting Directorate Manager, Rotorcraft & Services Management, P.O. Box 3707,
(i) Within the next 100 hours TIS or at the Directorate, Aircraft Certification Service. MC 2H–65, Seattle, WA 98124–2207;
next annual inspection, whichever occurs [FR Doc. 2015–06806 Filed 3–27–15; 8:45 am] telephone 206–544–5000, extension 1;
first, modify the LH and RH guidance units fax 206–766–5680; Internet https://
BILLING CODE 4910–13–P
and the lateral control lever by installing
www.myboeingfleet.com. You may view
bushings and washers to prevent shifting of
the bearings in the axial direction as follows:
this referenced service information at
(A) Remove and disassemble the RH
DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane
guidance unit and install a bushing, P/N Directorate, 1601 Lind Avenue SW.,
Federal Aviation Administration Renton, WA. For information on the
L672M1012260, between the lever and the
bracket as depicted in Detail B of Figure 4 of availability of this material at the FAA,
Eurocopter Alert Service Bulletin MBB
14 CFR Part 39 call 425–227–1221. It is also available
BK117 C–2–67A–010, Revision 3, dated [Docket No. FAA–2015–0498; Directorate on the Internet at http://www.
February 8, 2010 (BK117 ASB). Remove and Identifier 2014–NM–152–AD] regulations.gov by searching for and
disassemble the LH guidance unit and install locating Docket No. FAA–2015–0498.
a bushing, P/N L672M1012260, between the RIN 2120–AA64
lever and the bracket as depicted in Detail C Examining the AD Docket
Airworthiness Directives; The Boeing
of Figure 4 of BK117 ASB. You may examine the AD docket on
(B) Remove the lateral control lever and
Company Airplanes
the Internet at http://
install new bushings in accordance with the AGENCY: Federal Aviation www.regulations.gov by searching for
Accomplishment Instructions, paragraphs Administration (FAA), DOT.
3.C(9)(a) through 3.C(9)(g), of BK 117 ASB.
and locating Docket No. FAA–2015–
ACTION: Notice of proposed rulemaking 0498; or in person at the Docket
(C) Identify the modified lever assembly by
writing ‘‘MBB BK117 C–2–67A–010’’ on the (NPRM). Management Facility between 9 a.m.
lever with permanent marking pen and and 5 p.m., Monday through Friday,
SUMMARY: We propose to supersede except Federal holidays. The AD docket
protect with a single layer of lacquer (CM 421
or equivalent).
Airworthiness Directive (AD) 2007–16– contains this proposed AD, the
(D) Apply corrosion preventive paste (CM 08, which applies to all The Boeing regulatory evaluation, any comments
518 or equivalent) on the shank of the screws Company Model 747–100, 747–100B, received, and other information. The
and install airworthy parts as depicted in 747–100B SUD, 747–200B, 747–200C, street address for the Docket Office
Figure 5 of BK117 ASB. 747–300, 747–400, 747–400D, and (phone: 800–647–5527) is in the
(E) At intervals not to exceed 600 hours 747SR series airplanes. AD 2007–16–08 ADDRESSES section. Comments will be
TIS or 24 months, whichever occurs first, currently requires repetitive inspections available in the AD docket shortly after
inspect the bearings in the RH guidance unit, for cracking of the station 800 frame receipt.
LH guidance unit, and lateral control assembly, and repair if necessary. Since
guidance unit for play. If any bearing is loose, we issued AD 2007–16–08, we have FOR FURTHER INFORMATION CONTACT: Bill
replace the affected bearing with an received additional reports of cracks Ashforth, Aerospace Engineer, Airframe
airworthy bearing. found at the forward and aft inner chord Branch, ANM–120S, FAA, Seattle
strap and angles on the station 800 Aircraft Certification Office (ACO), 1601
(g) Alternative Methods of Compliance
(AMOCs) frame on the left-side and right-side Lind Avenue SW., Renton, WA 98057–
main entry doors. This proposed AD 3356; phone: 425–917–6432; fax: 425–
(1) The Manager, Safety Management 917–6590; email: bill.ashforth@faa.gov.
Group, FAA, may approve AMOCs for this would expand the inspection area. We
AD. Send your proposal to: Matt Fuller, are proposing this AD to detect and SUPPLEMENTARY INFORMATION:
Senior Aviation Safety Engineer, Safety correct fatigue cracks that could extend
and fully sever the frame, which could Comments Invited
Management Group, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth, result in development of skin cracks We invite you to send any written
Texas 76137; telephone (817) 222–5110; that could lead to rapid relevant data, views, or arguments about
email matthew.fuller@faa.gov. depressurization of the airplane. this proposed AD. Send your comments
(2) For operations conducted under a 14 DATES: We must receive comments on to an address listed under the
CFR part 119 operating certificate or under this proposed AD by May 14, 2015. ADDRESSES section. Include ‘‘Docket No.
14 CFR part 91, subpart K, we suggest that
ADDRESSES: You may send comments, FAA–2015–0498; Directorate Identifier
you notify your principal inspector, or
lacking a principal inspector, the manager of using the procedures found in 14 CFR 2014–NM–152–AD’’ at the beginning of
the local flight standards district office or 11.43 and 11.45, by any of the following your comments. We specifically invite
certificate holding district office before methods: comments on the overall regulatory,
operating any aircraft complying with this • Federal eRulemaking Portal: Go to economic, environmental, and energy
AD through an AMOC. http://www.regulations.gov. Follow the aspects of this proposed AD. We will
instructions for submitting comments. consider all comments received by the
(h) Additional Information
• Fax: 202–493–2251. closing date and may amend this
The subject of this AD is addressed in • Mail: U.S. Department of proposed AD because of those
European Aviation Safety Agency (EASA) AD comments.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Transportation, Docket Operations, M–
No. 2010–0058, dated March 30, 2010. You
30, West Building Ground Floor, Room We will post all comments we
may view the EASA AD on the Internet at
http://www.regulations.gov in Docket No.
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
FAA–2015–0674. Washington, DC 20590. www.regulations.gov, including any
• Hand Delivery: Deliver to Mail personal information you provide. We
(i) Subject address above between 9 a.m. and 5 will also post a report summarizing each
Joint Aircraft Service Component (JASC) p.m., Monday through Friday, except substantive verbal contact we receive
Code: 6710, Main Rotor Control. Federal holidays. about this proposed AD.
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![16608 Federal Register / Vol. 80, No. 60 / Monday, March 30, 2015 / Proposed Rules
PART 39—AIRWORTHINESS at the applicable times specified in paragraph (l) Related Information
DIRECTIVES 1.E., ‘‘Compliance,’’ of Boeing Alert Service (1) For more information about this AD,
Bulletin 747–53A2451, Revision 2, dated contact Bill Ashforth, Aerospace Engineer,
■ 1. The authority citation for part 39 June 13, 2014. Airframe Branch, ANM–120S, FAA, Seattle
continues to read as follows: (h) Repair of Cracking Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
Authority: 49 U.S.C. 106(g), 40113, 44701. If any cracking is found during any phone: 425–917–6432; fax: 425–917–6590;
inspection required by paragraph (g) of this email: bill.ashforth@faa.gov.
§ 39.13 [Amended]
AD, before further flight, repair the cracking (2) For service information identified in
■ 2. The FAA amends § 39.13 by using a method approved in accordance with this AD, contact Boeing Commercial
removing Airworthiness Directive (AD) the procedures specified in paragraph (k) of Airplanes, Attention: Data & Services
2007–16–08, Amendment 39–15147 (72 this AD. Management, P.O. Box 3707, MC 2H–65,
FR 44728, August 9, 2007), and adding Seattle, WA 98124–2207; telephone 206–
(i) Exception to the Service Information
the following new AD: 544–5000, extension 1; fax 206–766–5680;
(1) Where Boeing Alert Service Bulletin Internet https://www.myboeingfleet.com.You
The Boeing Company: Docket No. FAA– 747–53A2451, Revision 2, dated June 13, may view this referenced service information
2015–0498; Directorate Identifier 2014– 2014, specifies a compliance time ‘‘after the at the FAA, Transport Airplane Directorate,
NM–152–AD.
Revision 2 date of this service bulletin,’’ this 1601 Lind Avenue SW., Renton, WA. For
(a) Comments Due Date AD requires compliance within the specified information on the availability of this
The FAA must receive comments on this time after the effective date of this AD. material at the FAA, call 425–227–1221.
AD action by May 14, 2015. (2) The Condition column of paragraph Issued in Renton, Washington, on March
1.E., ‘‘Compliance,’’ of the Boeing Alert 19, 2015.
(b) Affected ADs Service Bulletin 747–53A2451, Revision 2,
Michael Kaszycki,
This AD replaces AD 2007–16–08, dated June 13, 2014, refers to total flight
Amendment 39–15147 (72 FR 44728, August cycles ‘‘as of the Revision 2 date of this Acting Manager, Transport Airplane
9, 2007). service bulletin.’’ This AD, however applies Directorate, Aircraft Certification Service.
to airplanes with the specified total flight [FR Doc. 2015–07081 Filed 3–27–15; 8:45 am]
(c) Applicability cycles or total flight hours as of the effective BILLING CODE 4910–13–P
This AD applies to all Boeing Model 747– date of this AD.
100, 747–100B, 747–100B SUD, 747–200B,
747–200C, 747–300, 747–400, 747–400D, and (j) Credit for Previous Actions
DEPARTMENT OF TRANSPORTATION
747SR series airplanes, certificated in any This paragraph provides credit for the
category. inspections and repairs of the inner chord Federal Aviation Administration
(d) Subject strap and angles of the station 800 frame
assembly between stringer 14 and stringer 18 14 CFR Part 39
Air Transport Association (ATA) of required by paragraphs (g) and (h) of this AD,
America Code 53, Fuselage. if those actions were performed before the [Docket No. FAA–2015–0676; Directorate
(e) Unsafe Condition effective date of this AD using Boeing Alert Identifier 2014–NM–164–AD]
Service Bulletin 747–53A2451, Revision 1,
This AD was prompted by reports of cracks RIN 2120–AA64
dated November 10, 2005.
found on the station 800 frame on the left-
side and right-side main entry doors (MED), (k) Alternative Methods of Compliance Airworthiness Directives; Bombardier,
at the forward and aft inner chord strap and (AMOCs) Inc. Airplanes
angles, which are outside the inspection area (1) The Manager, Seattle Aircraft
of AD 2007–16–08, Amendment 39–15147 AGENCY: Federal Aviation
Certification Office (ACO), FAA, has the
(72 FR 44728, August 9, 2007). We are Administration (FAA), DOT.
authority to approve AMOCs for this AD, if
issuing this AD to detect and correct fatigue ACTION: Notice of proposed rulemaking
requested using the procedures found in 14
cracks that could extend and fully sever the (NPRM).
CFR 39.19. In accordance with 14 CFR 39.19,
frame, which could result in development of
send your request to your principal inspector
skin cracks that could lead to rapid SUMMARY: We propose to adopt a new
or local Flight Standards District Office, as
depressurization of the airplane. airworthiness directive (AD) for certain
appropriate. If sending information directly
(f) Compliance to the manager of the ACO, send it to the Bombardier, Inc. Model BD–700–1A10
Comply with this AD within the attention of the person identified in and BD–700–1A11 airplanes. This
compliance times specified, unless already paragraph (k)(1) of this AD. Information may proposed AD was prompted by a report
done. be emailed to: 9-ANM-Seattle-ACO-AMOC- of several events where pilots
Requests@faa.gov. experienced difficulty in lateral control
(g) Inspections of Station 800 Frame (2) Before using any approved AMOC, of the airplane after doing a climb
Assembly Between Stringer 14 and Stringer notify your appropriate principal inspector,
30
through heavy rain conditions and a
or lacking a principal inspector, the manager
determination that the cause was water
Except as required by paragraph (i) of this of the local flight standards district office/
certificate holding district office. ingress in the aileron control pulley
AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing (3) An AMOC that provides an acceptable assembly. This proposed AD would
Alert Service Bulletin 747–53A2451, level of safety may be used for any repair require, for certain airplanes, inspecting
Revision 2, dated June 13, 2014: Do a required by this AD if it is approved by the for correct clearance and rework if
detailed inspection for cracking in the inner Boeing Commercial Airplanes Organization necessary, and, for certain other
chord strap, angles, and exposed web Designation Authorization (ODA) that has airplanes, installing a cover for the
adjacent to the inner chords, and do surface been authorized by the Manager, Seattle aileron pulley assembly. We are
tkelley on DSK3SPTVN1PROD with PROPOSALS
and open hole high-frequency eddy current ACO, to make those findings. For a repair proposing this AD to prevent water
(HFEC) inspections for cracking in the inner method to be approved, the repair must meet ingress in the aileron control pulley
chord strap and angles of the station 800 the certification basis of the airplane, and the
assembly, which could freeze in cold
frame assembly between stringer 14 and approval must specifically refer to this AD.
stringer 30, in accordance with the (4) AMOCs approved for AD 2007–16–08, conditions and result in reduced control
Accomplishment Instructions of Boeing Alert Amendment 39–15147 (72 FR 44728, August of the airplane.
Service Bulletin 747–53A2451, Revision 2, 9, 2007), are approved as AMOCs for the DATES: We must receive comments on
dated June 13, 2014. Repeat the inspections corresponding provisions of this AD. this proposed AD by May 14, 2015.
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Document Created: 2015-12-18 11:32:42
Document Modified: 2015-12-18 11:32:42
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by May 14, 2015. | |
| 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: [email protected] | |
| FR Citation | 80 FR 16606 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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