80 FR 34103 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 114 (June 15, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 114 (June 15, 2015)
| Page Range | 34103-34106 | |
| FR Document | 2015-14231 |
[Federal Register Volume 80, Number 114 (Monday, June 15, 2015)] [Proposed Rules] [Pages 34103-34106] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-14231] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1428; Directorate Identifier 2015-NM-026-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 adopt a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This proposed AD was prompted by reports of fatigue cracking of a certain chord of the pivot bulkhead. This proposed AD would require repetitive inspections for cracking of the left side and right side forward outer chords of the pivot bulkhead, and related investigative and corrective actions if necessary. This proposed AD provides a modification of the pivot bulkhead, which would terminate the repetitive inspections. We are proposing this AD to detect and correct fatigue cracking of the outer flanges of the left and right side forward outer chords of the pivot bulkhead, which could result in a severed forward outer chord and consequent loss of horizontal stabilizer control. DATES: We must receive comments on this proposed AD by July 30, 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; phone: 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-2015-1428. 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- 1428; 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: Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6513; 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 proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1428; Directorate Identifier 2015-NM-026-AD'' at the beginning of your comments. We specifically invite [[Page 34104]] 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. Discussion We received reports of fatigue cracking of the forward outer chord of the STA 2370 pivot bulkhead. Cracks in the forward outer chords of the STA 2370 pivot bulkhead that are not found and repaired can become large and result in a severed forward outer chord. The cracks were caused by a stress concentration, which is generated at the transition radius of the forward outer flange of the chord prior to the chord splice at the upper longeron. Since the horizontal stabilizer is attached to the STA 2370 bulkhead at two pivot locations, fatigue cracking of the outer flanges of the left and right side forward outer chords of the STA 2370 pivot bulkhead, if not corrected, could result in a severed forward outer chord and consequent loss of horizontal stabilizer control. Related Service Information Under 1 CFR Part 51 We reviewed the following Boeing service information. Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, describes procedures for repetitive detailed and high frequency eddy current (HFEC) inspections for cracking of the outer flanges of the left and right side forward outer chords of the STA 2370 pivot bulkhead, repetitive post-repair inspections for certain airplanes, and related investigative and corrective actions. Boeing Service Bulletin 777-53-0076, dated January 14, 2015, describes procedures for a modification of the STA 2370 pivot bulkhead by replacing the left and right side forward outer chords and upper splice angles, and related investigative and corrective actions. 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 NPRM. 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 these same type designs. Proposed AD Requirements 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.'' Refer to this service information for details on the procedures and compliance times. The phrase ``related investigative actions'' is used in this proposed AD. ``Related investigative actions'' are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Explanation of ``RC'' Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as RC (required for compliance) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. For service information that contains steps that are labeled as Required for Compliance (RC), the following provisions apply: (1) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD, and an AMOC is required for any deviations to RC steps, including substeps and identified figures; and (2) steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Differences Between This Proposed AD and the Service Information The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but 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 60 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 ---------------------------------------------------------------------------------------------------------------- Inspections of left and right Up to 15 work-hours $0 Up to $1,275 per Up to $76,500 per side pivot bulkhead forward x $85 per hour = inspection cycle. inspection cycle. chord. $1,275 per inspection cycle. Post-Repair Inspections.......... Up to 11 work-hours 0 Up to $935 per Up to $56,100 per x $85 per hour = inspection cycle. inspection cycle. $935 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- [[Page 34105]] We estimate the following costs to do any necessary repairs and modifications that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these actions: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Small crack repair................... Up to 45 work[dash]hours x (\1\) Up to $7,650. $85 per hour = $3,825 per side. Modification of the STA 2370 Pivot Up to 137 work[dash]hours x $34,086 Up to $45,731. Bulkhead (forward outer chord $85 per hour = $11,645. replacement). ---------------------------------------------------------------------------------------------------------------- \1\ We have received no definitive data that would enable us to provide parts cost estimates for the on- condition repair specified in this proposed AD. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 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 this 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: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2015-1428; Directorate Identifier 2015-NM-026-AD. (a) Comments Due Date We must receive comments by July 30, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777-200 and -300 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking of the forward outer chord of the station (STA) 2370 pivot bulkhead. We are issuing this AD to detect and correct fatigue cracking of the outer flanges of the left and right side forward outer chords of the STA 2370 pivot bulkhead, which could result in a severed forward outer chord and consequent loss of horizontal stabilizer control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions At the times specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, except as provided in paragraph (j)(1) of this AD: Do a detailed inspection and high frequency eddy current (HFEC) inspections for cracking of the left and right side forward outer chords of the STA 2370 pivot bulkhead, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777- 53A0075, dated January 14, 2015, except as provided in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable intervals specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, until the modification specified in paragraph (i) of this AD is done. (h) Post-Repair Inspections For airplanes on which a repair specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777- 53A0075 has been done: At the times specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, do a surface HFEC inspection, an open-hole HFEC inspection, and a detailed inspection for cracking of the left side and right side forward outer chords of the STA 2370 pivot bulkhead, and do all applicable related investigative and corrective actions, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, except as required by paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, until the modification specified in paragraph (i) of this AD is done. [[Page 34106]] (i) Terminating Action Modifying the STA 2370 pivot bulkhead by replacing the left and right side forward outer chords and upper splice angles, and doing all applicable related investigative and corrective actions, terminates the repetitive inspections required by paragraphs (g) and (h) of this AD for the modified location only. The modification must be done in accordance with the Accomplishment Instructions of Boeing Service Bulletin 777-53-0076, dated January 14, 2015, except as required by paragraph (j)(2) of this AD. (j) Exceptions to Service Bulletin Specifications (1) Where Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, specifies a compliance time ``after the Original Issue date of this Service Bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015; and Boeing Service Bulletin 777-530076, dated January 14, 2015; specify to contact Boeing for appropriate action, and Boeing Alert Service Bulletin 777-53A0075, dated January 14, 2015, specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (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: [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) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6513; 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; phone: 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 June 2, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-14231 Filed 6-12-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 34103
conclusively determined from that review. on the Internet at http://www.regulations.gov • Federal eRulemaking Portal: Go to
For any engine replaced as specified in the by searching for and locating Docket No. http://www.regulations.gov. Follow the
Airbus A318/A319/A320/A321 Aircraft FAA–2015–1429. instructions for submitting comments.
Maintenance Manual (AMM), Task 71–00– (2) For service information identified in • Fax: 202–493–2251.
00–400–040–A01, ‘‘Installation of the Power this AD, contact Airbus SAS, Airworthiness
Plant with Engine Positioner TWW 75E,’’ Office—EAW, 1 Rond Point Maurice
• Mail: U.S. Department of
dated May 2013: Within 6 months or 1,500 Bellonte, 31707 Blagnac Cedex, France; Transportation, Docket Operations, M–
flight cycles, whichever occurs first after the telephone: +33 5 61 93 36 96; fax: +33 5 61 30, West Building Ground Floor, Room
effective date of this AD, re-torque the 4 aft 93 44 51; email account.airworth-eas@ W12–140, 1200 New Jersey Avenue SE.,
mount pylon bolts using a method approved airbus.com; Internet http://www.airbus.com. Washington, DC 20590.
by the Manager, International Branch, ANM– You may view this service information at the • Hand Delivery: Deliver to Mail
116, Transport Airplane Directorate, FAA; or FAA, Transport Airplane Directorate, 1601 address above between 9 a.m. and 5
the European Aviation Safety Agency Lind Avenue SW., Renton, WA. For p.m., Monday through Friday, except
(EASA); or Airbus’ EASA Design information on the availability of this
Organization Approval (DOA). Federal holidays.
material at the FAA, call 425–227–1221.
Note 1 to paragraph (g) of this AD: For service information identified in
Additional guidance for the re-torque can be Issued in Renton, Washington, on June 3, this proposed AD, contact Boeing
found in Airbus A318/A319/A320/A321 2015. Commercial Airplanes, Attention: Data
AMM Temporary Revision 71–030, dated Michael Kaszycki, & Services Management, P. O. Box 3707,
March 14, 2014, or Airbus A318/A319/A320/ Acting Manager, Transport Airplane MC 2H–65, Seattle, WA 98124–2207;
A321 AMM Task 71–00–00–400–040–A01, Directorate, Aircraft Certification Service. phone: 206–544–5000, extension 1; fax:
‘‘Installation of the Power Plant with Engine [FR Doc. 2015–14228 Filed 6–12–15; 8:45 am] 206–766–5680; Internet https://
Positioner TWW 75E,’’ dated May 2014.
BILLING CODE 4910–13–P www.myboeingfleet.com. You may view
(h) Parts Installation Limitation this referenced service information at
As of the effective date of this AD, no the FAA, Transport Airplane
person may install a CFM56–5 engine, on any DEPARTMENT OF TRANSPORTATION Directorate, 1601 Lind Avenue SW.,
airplane, unless the engine is installed in Renton, WA. For information on the
accordance with the Accomplishment Federal Aviation Administration availability of this material at the FAA,
Instructions of Airbus Service Bulletin A320– call 425–227–1221. It is also available
71–1063, including Appendix 01, dated 14 CFR Part 39
August 13, 2014.
on the Internet at http://
[Docket No. FAA–2015–1428; Directorate www.regulations.gov by searching for
(i) Other FAA AD Provisions Identifier 2015–NM–026–AD] and locating Docket No. FAA–2015–
The following provisions also apply to this 1428.
AD: RIN 2120–AA64
(1) Alternative Methods of Compliance Examining the AD Docket
(AMOCs): The Manager, International Airworthiness Directives; The Boeing
You may examine the AD docket on
Branch, ANM–116, Transport Airplane Company Airplanes
the Internet at http://
Directorate, FAA, has the authority to
AGENCY: Federal Aviation www.regulations.gov by searching for
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Administration (FAA), DOT. and locating Docket No. FAA–2015–
In accordance with 14 CFR 39.19, send your ACTION: Notice of proposed rulemaking 1428; or in person at the Docket
request to your principal inspector or local (NPRM). Management Facility between 9 a.m.
Flight Standards District Office, as and 5 p.m., Monday through Friday,
appropriate. If sending information directly SUMMARY: We propose to adopt a new except Federal holidays. The AD docket
to the International Branch, send it to ATTN: airworthiness directive (AD) for certain contains this proposed AD, the
Sanjay Ralhan, Aerospace Engineer, The Boeing Company Model 777–200 regulatory evaluation, any comments
International Branch, ANM–116, Transport
and –300 series airplanes. This received, and other information. The
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; proposed AD was prompted by reports street address for the Docket Office
telephone: 425–227–1405; fax: 425–227– of fatigue cracking of a certain chord of (phone: 800–647–5527) is in the
1149. Information may be emailed to: 9- the pivot bulkhead. This proposed AD ADDRESSES section. Comments will be
ANM-116-AMOC-REQUESTS@faa.gov. would require repetitive inspections for available in the AD docket shortly after
Before using any approved AMOC, notify cracking of the left side and right side receipt.
your appropriate principal inspector, or forward outer chords of the pivot FOR FURTHER INFORMATION CONTACT:
lacking a principal inspector, the manager of bulkhead, and related investigative and
the local flight standards district office/
Narinder Luthra, Aerospace Engineer,
corrective actions if necessary. This Airframe Branch, ANM–120S, FAA,
certificate holding district office. The AMOC
approval letter must specifically reference proposed AD provides a modification of Seattle Aircraft Certification Office
this AD. the pivot bulkhead, which would (ACO), 1601 Lind Avenue SW., Renton,
(2) Contacting the Manufacturer: For any terminate the repetitive inspections. We WA 98057–3356; phone: 425–917–6513;
requirement in this AD to obtain corrective are proposing this AD to detect and fax: 425–917–6590; email:
actions from a manufacturer, the action must correct fatigue cracking of the outer narinder.luthra@faa.gov.
be accomplished using a method approved flanges of the left and right side forward
by the Manager, International Branch, ANM– SUPPLEMENTARY INFORMATION:
outer chords of the pivot bulkhead,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
116, Transport Airplane Directorate, FAA; or
which could result in a severed forward Comments Invited
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must outer chord and consequent loss of We invite you to send any written
include the DOA-authorized signature. horizontal stabilizer control. relevant data, views, or arguments about
DATES: We must receive comments on this proposal. Send your comments to
(j) Related Information
this proposed AD by July 30, 2015. an address listed under the ADDRESSES
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA ADDRESSES: You may send comments, section. Include ‘‘Docket No. FAA–
Airworthiness Directive 2014–0258, dated using the procedures found in 14 CFR 2015–1428; Directorate Identifier 2015–
November 28, 2014, for related information. 11.43 and 11.45, by any of the following NM–026–AD’’ at the beginning of your
This MCAI may be found in the AD docket methods: comments. We specifically invite
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We estimate the following costs to do that would be required based on the have no way of determining the number
any necessary repairs and modifications results of the proposed inspection. We of aircraft that might need these actions:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Small crack repair .......................................................... Up to 45 work-hours × $85 per hour = $3,825 per (1) Up to $7,650.
side.
Modification of the STA 2370 Pivot Bulkhead (forward Up to 137 work-hours × $85 per hour = $11,645 ........ $34,086 Up to $45,731.
outer chord replacement).
1 We have received no definitive data that would enable us to provide parts cost estimates for the on-condition repair specified in this proposed
AD.
According to the manufacturer, some (4) Will not have a significant in a severed forward outer chord and
of the costs of this proposed AD may be economic impact, positive or negative, consequent loss of horizontal stabilizer
covered under warranty, thereby on a substantial number of small entities control.
reducing the cost impact on affected under the criteria of the Regulatory (f) Compliance
individuals. We do not control warranty Flexibility Act. Comply with this AD within the
coverage for affected individuals. As a compliance times specified, unless already
List of Subjects in 14 CFR Part 39
result, we have included all costs in our done.
cost estimate. Air transportation, Aircraft, Aviation
safety, Incorporation by reference, (g) Inspections and Corrective Actions
Authority for This Rulemaking Safety. At the times specified in table 1 of
Title 49 of the United States Code paragraph 1.E., ‘‘Compliance,’’ of Boeing
specifies the FAA’s authority to issue The Proposed Amendment Alert Service Bulletin 777–53A0075, dated
Accordingly, under the authority January 14, 2015, except as provided in
rules on aviation safety. Subtitle I,
paragraph (j)(1) of this AD: Do a detailed
section 106, describes the authority of delegated to me by the Administrator, inspection and high frequency eddy current
the FAA Administrator. Subtitle VII: the FAA proposes to amend 14 CFR part (HFEC) inspections for cracking of the left
Aviation Programs, describes in more 39 as follows: and right side forward outer chords of the
detail the scope of the Agency’s STA 2370 pivot bulkhead, and do all
authority. PART 39—AIRWORTHINESS applicable related investigative and
We are issuing this rulemaking under DIRECTIVES corrective actions, in accordance with the
the authority described in Subtitle VII, Accomplishment Instructions of Boeing Alert
Part A, Subpart III, Section 44701: ■ 1. The authority citation for part 39 Service Bulletin 777–53A0075, dated January
‘‘General requirements.’’ Under that continues to read as follows: 14, 2015, except as provided in paragraph
Authority: 49 U.S.C. 106(g), 40113, 44701. (j)(2) of this AD. Do all applicable related
section, Congress charges the FAA with investigative and corrective actions before
promoting safe flight of civil aircraft in further flight. Repeat the inspections
§ 39.13 [Amended]
air commerce by prescribing regulations thereafter at the applicable intervals specified
for practices, methods, and procedures ■ 2. The FAA amends § 39.13 by adding
in table 1 of paragraph 1.E., ‘‘Compliance,’’
the Administrator finds necessary for the following new airworthiness of Boeing Alert Service Bulletin 777–
safety in air commerce. This regulation directive (AD): 53A0075, dated January 14, 2015, until the
is within the scope of that authority The Boeing Company: Docket No. FAA– modification specified in paragraph (i) of this
because it addresses an unsafe condition 2015–1428; Directorate Identifier 2015– AD is done.
that is likely to exist or develop on NM–026–AD. (h) Post-Repair Inspections
products identified in this rulemaking (a) Comments Due Date For airplanes on which a repair specified
action. We must receive comments by July 30, in Part 2 of the Accomplishment Instructions
2015. of Boeing Alert Service Bulletin 777–
Regulatory Findings 53A0075 has been done: At the times
We determined that this proposed AD (b) Affected ADs specified in table 2 of paragraph 1.E.,
would not have federalism implications None. ‘‘Compliance,’’ of Boeing Alert Service
under Executive Order 13132. This Bulletin 777–53A0075, dated January 14,
(c) Applicability 2015, do a surface HFEC inspection, an open-
proposed AD would not have a
This AD applies to The Boeing Company hole HFEC inspection, and a detailed
substantial direct effect on the States, on inspection for cracking of the left side and
Model 777–200 and –300 series airplanes,
the relationship between the national certificated in any category, as identified in right side forward outer chords of the STA
Government and the States, or on the Boeing Alert Service Bulletin 777–53A0075, 2370 pivot bulkhead, and do all applicable
distribution of power and dated January 14, 2015. related investigative and corrective actions,
responsibilities among the various in accordance with Part 3 of the
(d) Subject Accomplishment Instructions of Boeing Alert
levels of government.
Air Transport Association (ATA) of Service Bulletin 777–53A0075, dated January
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
For the reasons discussed above, I
certify this proposed regulation: America Code 53, Fuselage. 14, 2015, except as required by paragraph
(1) Is not a ‘‘significant regulatory (j)(2) of this AD. Do all applicable related
(e) Unsafe Condition investigative and corrective actions before
action’’ under Executive Order 12866, This AD was prompted by reports of further flight. Repeat the inspections
(2) Is not a ‘‘significant rule’’ under fatigue cracking of the forward outer chord of thereafter at the applicable times specified in
the DOT Regulatory Policies and the station (STA) 2370 pivot bulkhead. We table 2 of paragraph 1.E., ‘‘Compliance,’’ of
Procedures (44 FR 11034, February 26, are issuing this AD to detect and correct Boeing Alert Service Bulletin 777–53A0075,
1979), fatigue cracking of the outer flanges of the left dated January 14, 2015, until the
(3) Will not affect intrastate aviation and right side forward outer chords of the modification specified in paragraph (i) of this
in Alaska, and STA 2370 pivot bulkhead, which could result AD is done.
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![34106 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules
(i) Terminating Action (ii) Steps not labeled as RC may be prevent an ignition source in the fuel
Modifying the STA 2370 pivot bulkhead by deviated from using accepted methods in tank vapor space, which could result in
replacing the left and right side forward outer accordance with the operator’s maintenance a fuel tank explosion and consequent
chords and upper splice angles, and doing all or inspection program without obtaining
loss of the airplane.
applicable related investigative and approval of an AMOC, provided the RC steps,
corrective actions, terminates the repetitive including substeps and identified figures, can DATES: We must receive comments on
inspections required by paragraphs (g) and still be done as specified, and the airplane this proposed AD by July 30, 2015.
(h) of this AD for the modified location only. can be put back in an airworthy condition.
ADDRESSES: You may send comments,
The modification must be done in (l) Related Information using the procedures found in 14 CFR
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777– (1) For more information about this AD, 11.43 and 11.45, by any of the following
53–0076, dated January 14, 2015, except as contact Narinder Luthra, Aerospace Engineer, methods:
required by paragraph (j)(2) of this AD. Airframe Branch, ANM–120S, FAA, Seattle • Federal eRulemaking Portal: Go to
ACO, 1601 Lind Avenue SW., Renton, WA http://www.regulations.gov. Follow the
(j) Exceptions to Service Bulletin 98057–3356; phone: 425–917–6513; fax: 425–
Specifications 917–6590; email: narinder.luthra@faa.gov.
instructions for submitting comments.
(1) Where Boeing Alert Service Bulletin (2) For service information identified in • Fax: 202–493–2251.
777–53A0075, dated January 14, 2015, this AD, contact Boeing Commercial • Mail: U.S. Department of
specifies a compliance time ‘‘after the Airplanes, Attention: Data & Services Transportation, Docket Operations, M–
Original Issue date of this Service Bulletin,’’ Management, P.O. Box 3707, MC 2H–65, 30, West Building Ground Floor, Room
this AD requires compliance within the Seattle, WA 98124–2207; phone: 206–544– W12–140, 1200 New Jersey Avenue SE.,
specified compliance time after the effective 5000, extension 1; fax: 206–766–5680;
Internet https://www.myboeingfleet.com. You
Washington, DC 20590.
date of this AD.
(2) Although Boeing Alert Service Bulletin may view this referenced service information • Hand Delivery: U.S. Department of
777–53A0075, dated January 14, 2015; and at the FAA, Transport Airplane Directorate, Transportation, Docket Operations, M–
Boeing Service Bulletin 777–530076, dated 1601 Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room
January 14, 2015; specify to contact Boeing information on the availability of this W12–140, 1200 New Jersey Avenue SE.,
for appropriate action, and Boeing Alert material at the FAA, call 425–227–1221. Washington, DC, between 9 a.m. and 5
Service Bulletin 777–53A0075, dated January Issued in Renton, Washington, on June 2, p.m., Monday through Friday, except
14, 2015, specifies that action as ‘‘RC’’ 2015. Federal holidays.
(Required for Compliance), this AD requires
repair before further flight using a method Jeffrey E. Duven, For service information identified in
approved in accordance with the procedures Manager, Transport Airplane Directorate, this proposed AD, contact Fokker
specified in paragraph (k) of this AD. Aircraft Certification Service. Services B.V., Technical Services Dept.,
(k) Alternative Methods of Compliance [FR Doc. 2015–14231 Filed 6–12–15; 8:45 am] P.O. Box 1357, 2130 EL Hoofddorp, the
(AMOCs) BILLING CODE 4910–13–P Netherlands; telephone +31 (0)88–6280–
350; fax +31 (0)88–6280–111; email
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
technicalservices@fokker.com; Internet
authority to approve AMOCs for this AD, if DEPARTMENT OF TRANSPORTATION http://www.myfokkerfleet.com. You may
requested using the procedures found in 14 view this referenced service information
CFR 39.19. In accordance with 14 CFR 39.19, Federal Aviation Administration at the FAA, Transport Airplane
send your request to your principal inspector Directorate, 1601 Lind Avenue SW.,
or local Flight Standards District Office, as 14 CFR Part 39 Renton, WA. For information on the
appropriate. If sending information directly [Docket No. FAA–2015–1982; Directorate availability of this material at the FAA,
to the manager of the ACO, send it to the Identifier 2014–NM–108–AD] call 425–227–1221.
attention of the person identified in
paragraph (l)(1) of this AD. Information may RIN 2120–AA64 Examining the AD Docket
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov. Airworthiness Directives; Fokker You may examine the AD docket on
(2) Before using any approved AMOC, Services B.V. Airplanes the Internet at http://
notify your appropriate principal inspector, www.regulations.gov by searching for
or lacking a principal inspector, the manager AGENCY: Federal Aviation and locating Docket No. FAA–2015–
of the local flight standards district office/ Administration (FAA), DOT. 1982; or in person at the Docket
certificate holding district office. ACTION: Notice of proposed rulemaking Operations office between 9 a.m. and 5
(3) An AMOC that provides an acceptable (NPRM). p.m., Monday through Friday, except
level of safety may be used for any repair
Federal holidays. The AD docket
required by this AD if it is approved by the SUMMARY: We propose to adopt a new
Boeing Commercial Airplanes Organization contains this proposed AD, the
airworthiness directive (AD) for all regulatory evaluation, any comments
Designation Authorization (ODA) that has
Fokker Services B.V. Model F.28 Mark received, and other information. The
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair 1000, 2000, 3000, and 4000 airplanes. street address for the Docket Operations
method to be approved, the repair must meet This proposed AD was prompted by a office (telephone 800–647–5527) is in
the certification basis of the airplane, and the design review, which revealed that no the ADDRESSES section. Comments will
approval must specifically refer to this AD. controlled bonding provisions are be available in the AD docket shortly
(4) Except as required by paragraph (j)(2) present on a number of critical locations
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
after receipt.
of this AD: For service information that outside the fuel tank. This proposed AD
contains steps that are labeled as Required would require installing additional and FOR FURTHER INFORMATION CONTACT: Tom
for Compliance (RC), the provisions of improved fuel system bonding Rodriguez, Aerospace Engineer,
paragraphs (k)(4)(i) and (k)(4)(ii) apply.
provisions, and revising the airplane International Branch, ANM–116,
(i) The steps labeled as RC, including Transport Airplane Directorate, FAA,
substeps under an RC step and any figures maintenance or inspection program, as
applicable, by incorporating fuel 1601 Lind Avenue SW., Renton, WA
identified in an RC step, must be done to 98057–3356; telephone 425–227–1137;
comply with the AD. An AMOC is required airworthiness limitation items and
for any deviations to RC steps, including critical design configuration control fax 425–227–1149.
substeps and identified figures. limitations. We are proposing this AD to SUPPLEMENTARY INFORMATION:
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Document Created: 2015-12-15 15:14:01
Document Modified: 2015-12-15 15:14:01
| 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 July 30, 2015. | |
| Contact | Narinder Luthra, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6513; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 34103 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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