80 FR 51491 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 164 (August 25, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 164 (August 25, 2015)
| Page Range | 51491-51495 | |
| FR Document | 2015-20835 |
[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)] [Proposed Rules] [Pages 51491-51495] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-20835] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3147; Directorate Identifier 2014-NM-094-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 all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This proposed AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. This proposed AD would require an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would terminate the inspections. This proposed AD would also provide for optional terminating action for the repetitive inspections. We are proposing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane. [[Page 51492]] DATES: We must receive comments on this proposed AD by October 9, 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- 3147. 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- 3147; 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: Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6412; 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-2015-3147; Directorate Identifier 2014-NM-094-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. Discussion We have received reports of fractured forward attach fittings of the inboard flap outboard aft flap track, and it is believed to be the result of corrosion pits forming on the inside diameter of the fittings. Four operators have reported finding four fractured forward attach fittings of the aft flap track of the inboard flap on airplanes with approximately 20,300 to 31,900 total flight hours and approximately 5,900 to 8,500 total flight cycles. In addition, two operators reported three cracked fittings on airplanes with approximately 29,300 to 35,700 total flight hours and approximately 5,200 to 7,900 total flight cycles. This condition, if not corrected, could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. The service information describes procedures for an inspection for the affected part number and serial number of the main flap; various additional repetitive inspections of the fitting, if necessary; and replacement of the fitting or nested bushing installation, if necessary, which would eliminate the need for the inspections. 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 the same type design. 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. 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 Required for Compliance (RC) 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 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 Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, specifies groups 1, 2, 3, 4, and 5 airplanes as the effectivity. However, this proposed AD is applicable only to groups 1, 2, and 4 airplanes (Model 777-200, -200LR, -300, and -300ER airplanes) because the identified unsafe condition only affects these airplanes. For groups 3 and 5 airplanes (Model 777F airplanes), the [[Page 51493]] consequence of fitting fracture on these airplanes has not been determined to be an unsafe condition at this time. Therefore, we are not requiring inspections for groups 3 and 5 airplanes. We have coordinated this difference with Boeing. Costs of Compliance We estimate that this proposed AD affects 148 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspection to determine the part 3 work-hours x $85 per $0 $255..................... $37,740. number. hour = $255. Additional Inspections................ Up to 7 work[dash]hours x 0 Up to $595, per cycle.... Up to $88,060, per cycle. $85 per hour = $595, per cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that would be required based on the results of the proposed inspection. The nested bushing installation of the attach fitting and the fitting replacement are also optional terminating actions. We have no way of determining the number of aircraft on which these actions might be done. On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Nested bushing installation of the attach 40 work-hours x $85 per hour = $3,400. $45 $3,445. fitting. Fitting replacement........................... 73 work-hours x $85 per hour = $6,205. 7,400 13,605. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, all 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-2015-3147; Directorate Identifier 2014-NM-094-AD. (a) Comments Due Date We must receive comments by October 9, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of fractured forward attach fittings of the inboard flap outboard aft flap track. The fractured fittings were determined to be the result of corrosion pits forming on the inside diameter of the fittings. We are issuing this AD to detect and correct fracture of the fitting, which could result in the loss of the inboard aft flap and could lead to a punctured fuselage, causing injury to the flightcrew and passengers, and damage to the airplane. [[Page 51494]] (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine the Part Number At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014, except as provided by paragraph (l) of this AD: Do an inspection of the inboard flap of the main flap for affected part and serial numbers, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the inboard flap can be conclusively determined from that review. (h) Additional Inspections If any inboard flap of the main flap having an affected part number and serial number is found during the inspection required by paragraph (g) of this AD: Except as provided by paragraph (l) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014, do the inspections specified in paragraph (h)(1) or (h)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, until a terminating action in paragraph (k)(1), (k)(2), or (k)(3) of this AD is done. (1) At the forward attach fitting of the aft flap track of the inboard flap: Do a detailed inspection for cracking and bushing migration, and a high frequency eddy current inspection for cracking, in accordance with Part 2 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57- 0094, Revision 1, dated November 5, 2014. (2) At the forward attach fitting of the aft flap track of the inboard flap: Do a detailed inspection for cracking and bushing migration, and an ultrasound inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (i) Corrective Action for Bushing Migration If any bushing migration but no cracking is found during any inspection required by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do the actions specified in paragraphs (i)(1) through (i)(3) of this AD. Accomplishment of a terminating action specified in paragraph (i)(3) or (k) of this AD terminates the actions required by this paragraph. (1) Apply corrosion inhibiting compound BMS 3-23, Type II, around the bushing flanges on each side of the fitting, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. Re-apply the corrosion inhibiting compound at the time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (2) Repeat the inspections specified in paragraph (h)(1) or (h)(2) of this AD, except inspect for cracking only. (3) Do a terminating action specified in paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD. (i) Install a nested bushing to the forward attach fitting of the aft flap track of the inboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (ii) Replace the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (iii) Replace the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (j) Corrective Actions for Cracking If any cracking is found during any inspection required by paragraph (h) or (i)(3) of this AD: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, do a terminating action specified in paragraph (j)(1) or (j)(2) of this AD. Replacement of the forward attach fitting as specified in paragraph (j)(1) or (j)(2) of this AD terminates the actions in this AD. (1) Replace the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (2) Replace the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014. (k) Optional Terminating Actions (1) Installation of the nested bushing to the forward attach fitting of the aft flap track of the inboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD. (2) Replacement of the forward attach fitting of the aft flap track of the inboard flap with an aluminum fitting, in accordance with Part 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD. (3) Replacement of the forward attach fitting of the aft flap track of the inboard flap with a titanium fitting, in accordance with Part 6 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, terminates the requirements of this AD. (l) Exception to the Service Information Where Boeing Special Attention Service Bulletin 777-57-0094, Revision 1, dated November 5, 2014, 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. (m) Credit for Previous Actions (1) This paragraph provides credit for the actions specified in paragraphs (h)(1) and (h)(2) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777-57-0094, dated January 29, 2014, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions specified in paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Multi Operator Message MOM-MOM-13-0137-01B, dated February 21, 2013, which is not incorporated by reference in this AD. (n) 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 (o)(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) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (n)(4)(i) and (n)(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 [[Page 51495]] 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. (o) Related Information (1) For more information about this AD, contact Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6412; 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 August 17, 2015. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-20835 Filed 8-24-15; 8:45 am] BILLING CODE 4910-13-P
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between fuselage station 655 and station (j) Post-Modification Inspections and Renton, WA 98057–3356; phone: 425–917–
1434 that has a scribe line 0.001 inch or Corrective Action 6573; fax: 425–917–6590; email:
deeper. At the applicable time specified in Haytham.Aaidy@faa.gov.
(ii) Either an ultrasonic inspection or a paragraph 1.E., ‘‘Compliance,’’ of Boeing (2) For service information identified in
surface HFEC inspection for cracks Alert Service Bulletin 777–53A0052, dated this AD, contact Boeing Commercial
(depending on the location of the scribe October 10, 2014: Do a post-modification Airplanes, Attention: Data & Services
line(s)) of any skin panel common to a internal surface HFEC inspection for skin Management, P. O. Box 3707, MC 2H–65,
stringer lap splice between fuselage station cracks in the modified lap splices on both Seattle, WA 98124–2207; telephone 206–
655 and station 1434 that has a scribe line sides of the airplane; and do all applicable 544–5000, extension 1; fax 206–766–5680;
0.001 inch or deeper. corrective actions; in accordance with the Internet https://www.myboeingfleet.com. You
(iii) An external phased array ultrasonic Accomplishment Instructions of Boeing Alert may view this referenced service information
inspection for cracks in the lower/overlapped Service Bulletin 777–53A0052, dated October at the FAA, Transport Airplane Directorate,
skin of the stringer S–14L/R lap splices 10, 2014, except as provided by paragraph 1601 Lind Avenue SW., Renton, WA. For
between fuselage station 655 and station (h)(2) of this AD. Do all applicable corrective information on the availability of this
1434. actions before further flight. Repeat the material at the FAA, call 425–227–1221.
(iv) An open hole HFEC inspection for skin inspection of the modified lap splices Issued in Renton, Washington, on August
cracks at the upper and lower fastener rows thereafter at the applicable intervals specified 17, 2015.
of the stringer lap splices. in paragraph 1.E., ‘‘Compliance,’’ of Boeing
(3) Inspection ‘‘C’’ includes the inspections Kevin Hull,
Alert Service Bulletin 777–53A0052, dated
for scribe lines and cracks specified in October 10, 2014. Acting Manager, Transport Airplane
paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of Directorate, Aircraft Certification Service.
this AD on stringer S–14L/R lap splice (k) Alternative Methods of Compliance [FR Doc. 2015–20853 Filed 8–24–15; 8:45 am]
between fuselage station 655 and station (AMOCs)
BILLING CODE 4910–13–P
1434 on both sides of the airplane. (1) The Manager, Seattle Aircraft
(i) A detailed inspection for scribe lines. If Certification Office (ACO), FAA, has the
any scribe line is found during the inspection authority to approve AMOCs for this AD, if
requested using the procedures found in 14
DEPARTMENT OF TRANSPORTATION
required by this paragraph, the actions
include the inspections specified in CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
Federal Aviation Administration
paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this
AD. or local Flight Standards District Office, as
(A) A detailed inspection for cracks of the appropriate. If sending information directly 14 CFR Part 39
scribe line area(s). to the manager of the ACO, send it to the
attention of the person identified in [Docket No. FAA–2015–3147; Directorate
(B) Either an ultrasonic inspection or a
paragraph (l)(1) of this AD. Information may Identifier 2014–NM–094–AD]
surface HFEC inspection for cracks
(depending on the location of the scribe be emailed to: 9–ANM–Seattle–ACO–AMOC–
RIN 2120–AA64
line(s)). Requests@faa.gov.
(ii) An external phased array ultrasonic (2) Before using any approved AMOC,
notify your appropriate principal inspector,
Airworthiness Directives; The Boeing
inspection for cracks in the lower/overlapped
skin of the stringer lap splices between or lacking a principal inspector, the manager Company Airplanes
fuselage station 655 and station 1434. of the local flight standards district office/ AGENCY: Federal Aviation
(iii) An open hole HFEC inspection for skin certificate holding district office.
(3) An AMOC that provides an acceptable
Administration (FAA), DOT.
cracks at the upper and lower fastener rows
of the stringer S–14L/R lap splices. level of safety may be used for any repair ACTION: Notice of proposed rulemaking
required by this AD if it is approved by the (NPRM).
(h) Exceptions to Service Information Boeing Commercial Airplanes Organization
Specifications Designation Authorization (ODA) that has SUMMARY: We propose to adopt a new
(1) Where Paragraph 1.E., ‘‘Compliance,’’ of been authorized by the Manager, Seattle airworthiness directive (AD) for all The
Boeing Alert Service Bulletin 777–53A0052, ACO, to make those findings. For a repair Boeing Company Model 777–200,
dated October 10, 2014, specifies a method to be approved, the repair must meet –200LR, –300, and –300ER series
compliance time ‘‘after the original issue date the certification basis of the airplane, and the airplanes. This proposed AD was
of this service bulletin,’’ this AD requires approval must specifically refer to this AD.
prompted by reports of fractured
compliance within the specified compliance (4) Except as required by paragraph (h)(2)
time ‘‘after the effective date of this AD.’’ of this AD: For service information that forward attach fittings of the inboard
(2) If, during accomplishment of any contains steps that are labeled as Required flap outboard aft flap track. The
inspection required by this AD, any for Compliance (RC), the provisions of fractured fittings were determined to be
condition is found for which Boeing Alert paragraphs (k)(4)(i) and (k)(4)(ii) apply. the result of corrosion pits forming on
Service Bulletin 777–53A0052, dated October (i) The steps labeled as RC, including the inside diameter of the fittings. This
10, 2014, specifies to contact Boeing for substeps under an RC step and any figures proposed AD would require an
special repair instructions or supplemental identified in an RC step, must be done to inspection for the affected part number
instructions for the modification, and comply with the AD. An AMOC is required and serial number of the main flap;
specifies that action as ‘‘RC’’ (Required for for any deviations to RC steps, including
various additional repetitive inspections
Compliance): Before further flight, do the substeps and identified figures.
repair or modification using a method (ii) Steps not labeled as RC may be of the fitting, if necessary; and
approved in accordance with the procedures deviated from using accepted methods in replacement of the fitting or nested
specified in paragraph (k) of this AD. accordance with the operator’s maintenance bushing installation, if necessary, which
or inspection program without obtaining would terminate the inspections. This
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(i) Lap Splice Modification approval of an AMOC, provided the RC steps, proposed AD would also provide for
At the applicable time specified in including substeps and identified figures, can optional terminating action for the
paragraph 1.E., ‘‘Compliance,’’ of Boeing still be done as specified, and the airplane repetitive inspections. We are proposing
Alert Service Bulletin 777–53A0052, dated can be put back in an airworthy condition. this AD to detect and correct fracture of
October 10, 2014: Do the left-side and right-
side lap splice modification, in accordance (l) Related Information the fitting, which could result in the
with the Accomplishment Instructions of (1) For more information about this AD, loss of the inboard aft flap and could
Boeing Alert Service Bulletin 777–53A0052, contact Haytham Alaidy, Aerospace lead to a punctured fuselage, causing
dated October 10, 2014, except as provided Engineer, Airframe Branch, ANM–120S, injury to the flightcrew and passengers,
by paragraph (h)(2) of this AD. FAA, Seattle ACO, 1601 Lind Avenue SW., and damage to the airplane.
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consequence of fitting fracture on these We have coordinated this difference Costs of Compliance
airplanes has not been determined to be with Boeing. We estimate that this proposed AD
an unsafe condition at this time. affects 148 airplanes of U.S. registry.
Therefore, we are not requiring We estimate the following costs to
inspections for groups 3 and 5 airplanes. comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection to determine the 3 work-hours × $85 per hour = $0 $255 ........................................ $37,740.
part number. $255.
Additional Inspections ............. Up to 7 work-hours × $85 per 0 Up to $595, per cycle ............. Up to $88,060, per cycle.
hour = $595, per cycle.
We estimate the following costs to do bushing installation of the attach fitting aircraft on which these actions might be
any necessary replacements that would and the fitting replacement are also done.
be required based on the results of the optional terminating actions. We have
proposed inspection. The nested no way of determining the number of
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Nested bushing installation of the attach fitting ................ 40 work-hours × $85 per hour = $3,400 .......................... $45 $3,445.
Fitting replacement ........................................................... 73 work-hours × $85 per hour = $6,205 .......................... 7,400 13,605.
According to the manufacturer, all of proposed AD would not have a Authority: 49 U.S.C. 106(g), 40113, 44701.
the costs of this proposed AD may be substantial direct effect on the States, on
§ 39.13 [Amended]
covered under warranty, thereby the relationship between the national
reducing the cost impact on affected Government and the States, or on the ■ 2. The FAA amends § 39.13 by adding
individuals. We do not control warranty distribution of power and the following new airworthiness
coverage for affected individuals. As a responsibilities among the various directive (AD):
result, we have included all costs in our levels of government. The Boeing Company: Docket No. FAA–
cost estimate. For the reasons discussed above, I 2015–3147; Directorate Identifier 2014–
certify this proposed regulation: NM–094–AD.
Authority for This Rulemaking (1) Is not a ‘‘significant regulatory
Title 49 of the United States Code action’’ under Executive Order 12866, (a) Comments Due Date
specifies the FAA’s authority to issue (2) Is not a ‘‘significant rule’’ under We must receive comments by October 9,
rules on aviation safety. Subtitle I, the DOT Regulatory Policies and 2015.
section 106, describes the authority of Procedures (44 FR 11034, February 26,
(b) Affected ADs
the FAA Administrator. Subtitle VII: 1979),
Aviation Programs, describes in more (3) Will not affect intrastate aviation None.
detail the scope of the Agency’s in Alaska, and (c) Applicability
authority. (4) Will not have a significant
economic impact, positive or negative, This AD applies to all The Boeing
We are issuing this rulemaking under Company Model 777–200, –200LR, –300, and
the authority described in Subtitle VII, on a substantial number of small entities
–300ER series airplanes, certificated in any
Part A, Subpart III, Section 44701: under the criteria of the Regulatory
category.
‘‘General requirements.’’ Under that Flexibility Act.
section, Congress charges the FAA with (d) Subject
List of Subjects in 14 CFR Part 39
promoting safe flight of civil aircraft in Air Transport Association (ATA) of
air commerce by prescribing regulations Air transportation, Aircraft, Aviation America Code 57, Wings.
for practices, methods, and procedures safety, Incorporation by reference,
Safety. (e) Unsafe Condition
the Administrator finds necessary for
This AD was prompted by reports of
safety in air commerce. This regulation The Proposed Amendment fractured forward attach fittings of the
is within the scope of that authority
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Accordingly, under the authority inboard flap outboard aft flap track. The
because it addresses an unsafe condition delegated to me by the Administrator, fractured fittings were determined to be the
that is likely to exist or develop on the FAA proposes to amend 14 CFR part result of corrosion pits forming on the inside
products identified in this rulemaking 39 as follows: diameter of the fittings. We are issuing this
action. AD to detect and correct fracture of the
Regulatory Findings PART 39—AIRWORTHINESS fitting, which could result in the loss of the
DIRECTIVES inboard aft flap and could lead to a
We determined that this proposed AD punctured fuselage, causing injury to the
would not have federalism implications ■ 1. The authority citation for part 39 flightcrew and passengers, and damage to the
under Executive Order 13132. This continues to read as follows: airplane.
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![Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules 51495
or inspection program without obtaining updates into the airplane flight manual Comments Invited
approval of an AMOC, provided the RC steps, (AFM) and/or the pilot operating
including substeps and identified figures, can We invite you to send any written
handbook (POH) that will clearly relevant data, views, or arguments about
still be done as specified, and the airplane establish that the NTS is not designed
can be put back in an airworthy condition. this proposal. Send your comments to
to automatically feather the propeller an address listed under the ADDRESSES
(o) Related Information but only to provide drag protection. We section. Include ‘‘Docket No. FAA–
(1) For more information about this AD, are proposing this AD to correct the 2015–3607; Directorate Identifier 2015–
contact Eric Lin, Aerospace Engineer, unsafe condition on these products. CE–010–AD’’ at the beginning of your
Airframe Branch, ANM–120S, FAA, Seattle DATES: We must receive comments on comments. We specifically invite
Aircraft Certification Office, 1601 Lind
this proposed AD by October 9, 2015. comments on the overall regulatory,
Avenue SW., Renton, WA 98057–3356;
telephone: 425–917–6412; fax: 425–917– ADDRESSES: You may send comments, economic, environmental, and energy
6590; email: Eric.Lin@faa.gov. using the procedures found in 14 CFR aspects of this proposed AD. We will
(2) For service information identified in 11.43 and 11.45, by any of the following consider all comments received by the
this AD, contact Boeing Commercial methods: closing date and may amend this
Airplanes, Attention: Data & Services • Federal eRulemaking Portal: Go to proposed AD because of those
Management, P.O. Box 3707, MC 2H–65, comments.
http://www.regulations.gov. Follow the
Seattle, WA 98124–2207; telephone 206– We will post all comments we
544–5000, extension 1; fax 206–766–5680; instructions for submitting comments.
• Fax: 202–493–2251. receive, without change, to http://
Internet https://www.myboeingfleet.com. You www.regulations.gov, including any
may view this referenced service information • Mail: U.S. Department of
personal information you provide. We
at the FAA, Transport Airplane Directorate, Transportation, Docket Operations, M–
1601 Lind Avenue SW., Renton, WA. For will also post a report summarizing each
30, West Building Ground Floor, Room
information on the availability of this substantive verbal contact we receive
W12–140, 1200 New Jersey Avenue SE.,
material at the FAA, call 425–227–1221. about this proposed AD.
Washington, DC 20590.
Issued in Renton, Washington, on August • Hand Delivery: Deliver to Mail Discussion
17, 2015. address above between 9 a.m. and 5 The FAA received a report of an
Kevin Hull, p.m., Monday through Friday, except accident where an M7 Aerospace LLC
Acting Manager, Transport Airplane
Federal holidays. Model SA227–AC airplane experienced
Directorate, Aircraft Certification Service. For service information identified in left engine power loss and consequent
[FR Doc. 2015–20835 Filed 8–24–15; 8:45 am] this proposed AD, contact M7 loss of control. Training manuals
BILLING CODE 4910–13–P
Aerospace LLC, 10823 NE Entrance provide descriptions of the negative
Road, San Antonio, Texas 78216; phone: torque system (NTS), which provides
(210) 824–9421; fax: (210) 804–7766; partial anti-drag protection if a negative
DEPARTMENT OF TRANSPORTATION Internet: http://www.elbitsystems- torque condition is sensed. This feature
us.com; email: MetroTech@ might cause pilots to assume the system
Federal Aviation Administration M7Aerospace.com. You may view this automatically provides full anti-drag
referenced service information at the protection in the event of an engine
14 CFR Part 39 FAA, Small Airplane Directorate, 901 failure or power loss. The pilot must
Locust, Kansas City, Missouri 64106. also take prompt action to fully feather
[Docket No. FAA–2015–3607; Directorate For information on the availability of
Identifier 2015–CE–010–AD] the propeller on the failed engine to
this material at the FAA, call 816–329– reduce drag. A pilot’s sole reliance on
RIN 2120–AA64 4148. the NTS for reducing drag in the event
Examining the AD Docket of engine power loss may result in the
Airworthiness Directives; M7 pilot’s failure to initiate the Engine
Aerospace LLC Airplanes You may examine the AD docket on Failure Inflight checklist and feather the
the Internet at http:// propellers in time.
AGENCY: Federal Aviation www.regulations.gov by searching for
Administration (FAA), DOT. This condition, if not corrected, could
and locating Docket No. FAA–2015– result in loss of control of the aircraft
ACTION: Notice of proposed rulemaking 3607; or in person at the Docket due to excessive asymmetric drag.
(NPRM). Management Facility between 9 a.m.
and 5 p.m., Monday through Friday, Related Service Information Under 1
SUMMARY: We propose to adopt a new CFR Part 51
except Federal holidays. The AD docket
airworthiness directive (AD) for all M7
contains this proposed AD, the We reviewed the following M7
Aerospace LLC Models SA26–AT,
regulatory evaluation, any comments Aerospace LLC AFM revisions:
SA226–T, SA226–AT, SA226–T(B), • AFM revision dated May 14, 2015,
received, and other information. The
SA226–TC, SA227–AT, SA227–TT, section III, SA26–AT Dash One;
street address for the Docket Office
SA227–AC (C–26A), SA227–BC (C– • AFM revision dated May 14, 2015,
(phone: 800–647–5527) is in the
26A), SA227–CC, and SA227–DC (C– section III, SA26–AT Dash Two;
ADDRESSES section. Comments will be
26B) airplanes. This proposed AD was
available in the AD docket shortly after • AFM revision B–33, sections i and
prompted by information that the
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
receipt. III, SA226–AT, dated November 14,
airplane flight manual (AFM) does not 2014;
FOR FURTHER INFORMATION CONTACT:
provide adequate guidance in the • AFM revision A–29, sections i and
handling of engine failures, which may Michael Heusser, Aerospace Engineer, III, SA226–T, dated November 14, 2014;
lead to reliance on the negative torque FAA, Fort Worth Aircraft Certification • AFM revision B–29, sections i and
system (NTS) for reducing drag. This Office, 2601 Meacham Blvd., Fort 3, SA226–T(B), dated November 14,
condition could lead the pilot to not Worth, Texas 76137; telephone: (817) 2014;
fully feather the propeller with 222–5038; fax: (817) 222–5960; email: • AFM revision A–43, sections i and
consequent loss of control. This Michael.A.Heusser@faa.gov. III, SA226–TC, dated November 14,
proposed AD would require inserting SUPPLEMENTARY INFORMATION: 2014;
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Document Created: 2018-02-23 11:03:02
Document Modified: 2018-02-23 11:03:02
| 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 October 9, 2015. | |
| Contact | Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917-6412; fax: 425- 917-6590; email: [email protected] | |
| FR Citation | 80 FR 51491 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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