Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters, 44045-44048 [2013-17629]

Download as PDF Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules would require 0.5 work-hour, for a cost of $43 per helicopter. The labor cost of installing paper in the flight manual would be negligible for a helicopter. • Replacing the MRH assembly would require 24 work-hours and parts would cost $5,000, for a total cost of $7,040 per helicopter. ehiers on DSK2VPTVN1PROD with PROPOSALS-1 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, 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 to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by Reference, Safety. VerDate Mar<15>2010 15:39 Jul 22, 2013 Jkt 229001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ EUROCOPTER FRANCE HELICOPTERS (Eurocopter): Docket No. FAA–2013– 0635; Directorate Identifier 2012–SW– 081–AD. (a) Applicability This AD applies to Eurocopter Model EC225LP helicopters with a main rotor hub (MRH) assembly with a rotating swashplate, part number (P/N) 332A31–3074–00 or 332A31–3076–00, and stationary swashplate, P/N 332A31–3079–00 or 332A31–3079–01, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as corrosion or a crack in the stationary or rotating swashplate of the MRH assembly, which could lead to failure of the swashplate and subsequent loss of helicopter control. (c) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (d) Required Actions (1) Within 110 hours time-in-service (TIS) or before the MRH assembly accumulates 1,320 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 1,320 hours TIS, visually inspect the rotating and stationary swashplates for corrosion or a crack by following the Accomplishment Instructions, paragraph 3.B.2 and Figures 1 through 3, of Eurocopter Alert Service Bulletin No. EC225–05A030, Revision 0, dated July 12, 2012 (ASB). (2) If a crack exists in the rotating or stationary swashplates, replace the MRH assembly with an airworthy MRH. (3) If corrosion exists without any visual indication of cracking, do the following: (i) Before further flight, install a placard stating ‘‘NO FLIGHT IN OAT BELOW ¥30 °C’’ in the full view of the pilots and add the statement ‘‘NO FLIGHT IN OAT BELOW ¥30 °C’’ to the Operating Limitations Section of the helicopter’s Rotorcraft Flight Manual (RFM) by making pen and ink changes or by inserting a copy of this AD in Section 2.3 Flight Envelope, Item 2 Temperature Limits. (ii) Within 150 hours TIS or 6 months after the inspection when the corrosion was first detected, whichever occurs first, replace the MRH assembly with an airworthy assembly. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 44045 Remove any placard that states ‘‘NO FLIGHT IN OAT BELOW ¥30 °C’’ from the helicopter and remove any related limitation from the RFM. (4) Replacement of an MRH assembly does not constitute terminating action for the repetitive inspections required by paragraph (d)(1) of this AD. (e) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov. (2) For operations conducted under a 14 CFR Part 119 operating certificate or under 14 CFR Part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (f) Additional Information The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD No. 2012–0131, dated July 31, 2012. You may view a copy of the EASA AD in the AD Docket on the Internet at https:// www.regulations.gov. (g) Subject Joint Aircraft Service Component (JASC) Code: 6230, Main Rotor Mast/Swashplate. Issued in Fort Worth, Texas, on July 11, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–17628 Filed 7–22–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0636; Directorate Identifier 2012–SW–065–AD] RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Sikorsky Model S–70, S–70A, and S– 70C helicopters. This proposed AD would establish a new life limit based SUMMARY: E:\FR\FM\23JYP1.SGM 23JYP1 44046 Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules ehiers on DSK2VPTVN1PROD with PROPOSALS-1 on a prorated formula for certain identified components (parts) installed on Model S–70, S–70A, and S–70C helicopters after being previously installed on certain military model helicopters. This proposed AD is prompted by the discovery that certain parts have been interchanged between military helicopter models with different life limits and the possibility that these same parts can be interchanged with civilian models with different life limits. The proposed actions are intended to establish a prorated in service life limit for each identified part to prevent fatigue failure of a part and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by September 23, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7156; email michael.davison@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also VerDate Mar<15>2010 15:39 Jul 22, 2013 Jkt 229001 invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion We propose to adopt a new AD for Sikorsky Model S–70, S–70A and S–70C helicopters. Certain parts on Model S– 70, S–70A, and S–70C helicopters are common to military Model UH–60M and SH–60B/F helicopters. These parts have identical part numbers. However, the part life limits may be different on the military models and are often lower due to higher usage and flight load spectrum. This proposed AD is prompted by the discovery that personnel at a military depot had installed military Model UH–60M parts on military Model UH–60A/L helicopters. Because the civilian Model S–70 series helicopters are derived from the military Model UH–60, it is possible that parts previously installed on military aircraft with a lower life limit could inadvertently be later installed on civil aircraft. This proposed AD would require establishing a pro-rated life limit for each affected part to account for the heavier usage when previously installed on the Model UH–60M or SH–60B/F. The proposed actions are intended to establish appropriate remaining inservice lives to identified parts to prevent fatigue failure of a part and subsequent loss of control of the helicopter. FAA’s Determination We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition exists and is likely to PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 exist or develop on other helicopters of this same type design. Proposed AD Requirements This proposed AD would require, within 25 hours time-in-service, inserting the component life prorating formula into the airworthiness limitation section of the maintenance manual or instructions for continued airworthiness, calculating the new life limit for each part by applying the formula, and establishing life limits for certain parts without applying the formula. Furthermore, the proposed AD would require updating the component log or equivalent record with the new in-service life limit. This proposed AD would also require replacing each part that has reached or exceeded its new life limit with an airworthy part. Lastly, this proposed AD would prohibit installing any applicable part on a Model S–70, S– 70A, or S–70C helicopter if the number of hours is unknown and would prohibit installing certain parts on a Model S–70, S–70A, or S–70C helicopter if they have been previously installed on a Model UH–60M helicopter. Costs of Compliance We estimate that this proposed AD would affect 9 helicopters of U.S. Registry. We estimate that the cost to insert the pages into the TM would be negligible. 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 E:\FR\FM\23JYP1.SGM 23JYP1 Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules 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, 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 to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Sikorsky Aircraft Corporation (Sikorsky): Docket No. FAA–2013–0636; Directorate Identifier 2012–SW–065–AD. (a) Applicability This AD applies to Model S–70, S–70A, and S–70C helicopters, certificated in any category, with the following parts installed: (1) Spindle and liner assembly, part number (P/N) 38023–10374–041; (2) Main Rotor Hub, P/N 70070–10046–055 and –056; (3) Main Rotor Spindle nut, P/N 70102– 08105–102; (4) Main Rotor Control Horn, P/N 70102– 08111–047; (5) Main Rotor Hub, P/N 70103–08112–041 and –047; (6) Rotating Swashplate, P/N 70104– 08001–044 and –045; (7) Main rotor Shaft Extension, P/N 70351– 08186–043; (8) Main Rotor Gear Box Housing, P/N 70351–38110–043, –044, and –045; (9) Main Rotor Shaft, P/N 70351–38131– 042; (10) Output Bevel Gear and Shaft, P/N 70358–06620–101 and –102; (11) Left Tie Rod Assembly, P/N 70400– 08115–043, –045, –046, and –047; (12) Forward Bellcrank Support Assembly, P/N 70400–08162–042; 44047 (13) Lateral Servo Bellcrank, P/N 70400– 08166–041; or (14) Tail rotor Servo Assembly, P/N 70410– 06520–044 through –046. (b) Unsafe Condition This AD defines the unsafe condition as a critical part remaining in service beyond its life limit due to previously being installed on a different helicopter model with higher usage and flight loads. This condition could result in fatigue failure of a critical part and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by September 23, 2013. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 25 hours time-in-service (TIS): (i) Insert into the airworthiness limitation section of the maintenance manual or instructions for continued airworthiness the component life prorating formula in Section 1.1.3 of Sikorsky Technical Manual TM 1– 70–23AW–2, Change 3, dated April 15, 2012. (ii) Using the service life limits in Table 1 to paragraph (e) of this AD, apply the component life prorating formula and calculate the new life limit for each specified part. If the number of hours of a part is unknown, that part cannot be installed on a Sikorsky Model S–70, S–70A, or S–70C helicopter. Do not calculate a new life limit for the part where the Model SH–60 life limit is higher than the life limit on Models S–70, S–70A, and S–70C. TABLE 1 TO PARAGRAPH (e) P/N ................................................. and –056 ................................ ................................................. ................................................. Spindle and Liner Assembly .................... Main Rotor Hub ....................................... Main Rotor Spindle Nut ........................... Main Rotor Control Horn ......................... 70103–08112–041 and –047 ................................ 70104-08001-044-045 ........................................... 70351–08186–043 ................................................. 70351–38110–043, –044, and –045 ..................... 70351–38131–042 ................................................. 70358–06620–101 and –102 ................................ 70400–08115–043, –045, –046, and -047 ............ 70400–08162–042 ................................................. 70400–08166–041 ................................................. 70410–06520–044 through –046 .......................... ehiers on DSK2VPTVN1PROD with PROPOSALS-1 38023–10374–041 70070–10046–055 70102–08105–102 70102–08111–047 S–70, S–70A, S–70C Service life Part description Main Rotor Hub ....................................... Rotating Swashplate ................................ Main Rotor Shaft Extension ..................... Main Rotor Gear Box Housing ................ Main Rotor Shaft ...................................... Output Bevel Gear and Shaft .................. Left Tie Rod Assembly ............................ Forward Bellcrank Support Assembly ..... Lateral Servo Bellcrank ........................... Tail Rotor Servo Assembly ...................... 8,000 5,100 8,000 20,000/1,300 2/ 2,500 2 5,100 11,000 14,000 11,000 17,000 5,000 14,000 14,000/2,500 3 20,000 15,000 UH–60M Service life SH–60B/F Service life 6,400 3,100 6,400 10,000 10,000 N/A 1 10,000 N/A 1 3,100 4,600 4,900 4,000 5,200 1,800 4,600 5,600 11,000 11,000 N/A 1 9,600 16,000 9,000 19,000 N/A 1 6,300 7,600 14,000 N/A 1 1 There is no service life limit listed because the parts on Model SH–60B/F have a different P/N than the parts on Models S–70, S–70A, and S–70C. 2 For serial number (S/N) 32479930 through 324791859, with CAGE code 60078, the life limit is 1,300 hours TIS. For S/N A241–07543 through A241–07594, A241-07706 through A241–07755, A241-07768 through A241–07771, A241–07800 through A241– 07831, R241–00101 through R241–00355, R241–00701 through R241-00966, and R241–01001 through R241-01166, the life limit is 2,500 hours TIS. 3 For S/N A–367–00001 through A367–00035, with CAGE code 78286, the life limit is 2,500 hours TIS. VerDate Mar<15>2010 15:39 Jul 22, 2013 Jkt 229001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 E:\FR\FM\23JYP1.SGM 23JYP1 44048 Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules (iii) Record the newly-established life limit of each part on the part’s component log card or equivalent record. (2) After establishing the new life limit, replace each part that has reached or exceeded its new life limit with an airworthy part before further flight. (3) Do not install the following parts on a Model S–70, S–70A, or S–70C helicopter if they have been previously installed on a Model UH–60M helicopter: (i) Bolt, self retaining, P/N 70103–08801– 102; (ii) Bifilar, P/N 70107–08400–046; (iii) Aft Bellcrank, P/N 70400–08102–045; (iv) Aft Walking Beam Assembly, P/N 70400–08104–048; or (v) Close Tolerance Bolt, P/N 70400– 26802–102 and –103. (f) Alternative Methods of Compliance (AMOC) (1) The Manager, Boston Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Davison, Flight Test Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7156; email michael.davison@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. We propose to supersede an existing airworthiness directive (AD) for Sikorsky Model S–76A, B, and C helicopters. The existing AD currently requires inspecting the main rotor lower bifilar arm assembly (bifilar arm assembly) for a crack, and if there is a crack, replacing the bifilar arm assembly. The AD also requires a onetime test for the correct torque on the lug nuts, and if necessary, conducting torque stabilization tests. Since we issued that AD, Sikorsky has developed a terminating procedure for the inspections required by the existing AD. This proposed AD would retain the requirements of that AD, and would require replacing the main rotor hub (MRH) pilot with a different partnumbered MRH pilot, which would be terminating action for the requirements of the AD. The proposed actions are intended to prevent failure of a bifilar lug, damage to the main rotor control system, and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by September 23, 2013. SUMMARY: Issued in Fort Worth, Texas, on July 11, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. [FR Doc. 2013–17629 Filed 7–22–13; 8:45 am] Examining the AD Docket BILLING CODE 4910–13–P You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the economic evaluation, any comments received and other information. The street address for the Docket Operations Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed AD, contact Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT 06614; telephone (800) (g) Subject Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor Hub, 6230 Main Rotor Mast/Swashplate, 6320 Main Rotor Gearbox, 6310 Engine/Transmission Coupling, 6510 Tail Rotor Drive Shaft. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0637; Directorate Identifier 2013–SW–030–AD] ehiers on DSK2VPTVN1PROD with PROPOSALS-1 RIN 2120–AA64 Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: VerDate Mar<15>2010 15:39 Jul 22, 2013 Jkt 229001 ADDRESSES: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 562–4409; email tsslibrary@sikorsky.com; or at https:// www.sikorsky.com. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Nicholas Faust, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, Massachusetts 01803; telephone (781) 238–7763; email nicholas.faust@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion On October 26, 2005, we issued AD 2005–22–01, amendment 39–14345 (70 FR 61721) for Sikorsky Model S–76A, B, and C helicopters with an MRH pilot part number (P/N) 76103–08003–101 with 1,500 or more hours time-inservice (TIS) installed. The AD requires, every 50 hours TIS, inspecting the main rotor lower bifilar arm assembly in the attachment area around the lower bifilar lugs for a crack. If there is a crack, the AD requires replacing the bifilar arm assembly. If there is not a crack, the AD requires a one-time test for the correct torque on the lug nuts, and if necessary, conducting torque stabilization tests. The AD was prompted by four reports E:\FR\FM\23JYP1.SGM 23JYP1

Agencies

[Federal Register Volume 78, Number 141 (Tuesday, July 23, 2013)]
[Proposed Rules]
[Pages 44045-44048]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-17629]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0636; Directorate Identifier 2012-SW-065-AD]
RIN 2120-AA64

Airworthiness Directives; Sikorsky Aircraft Corporation
(Sikorsky) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for
Sikorsky Model S-70, S-70A, and S-70C helicopters. This proposed AD
would establish a new life limit based

[[Page 44046]]

on a prorated formula for certain identified components (parts)
installed on Model S-70, S-70A, and S-70C helicopters after being
previously installed on certain military model helicopters. This
proposed AD is prompted by the discovery that certain parts have been
interchanged between military helicopter models with different life
limits and the possibility that these same parts can be interchanged
with civilian models with different life limits. The proposed actions
are intended to establish a pro-rated in service life limit for each
identified part to prevent fatigue failure of a part and subsequent
loss of control of the helicopter.

DATES: We must receive comments on this proposed AD by September 23,
2013.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the economic
evaluation, any comments received, and other information. The street
address for the Docket Operations Office (telephone 800-647-5527) is in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer,
Boston Aircraft Certification Office, Engine & Propeller Directorate,
12 New England Executive Park, Burlington, Massachusetts 01803;
telephone (781) 238-7156; email michael.davison@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to participate in this rulemaking by submitting
written comments, data, or views. We also invite comments relating to
the economic, environmental, energy, or federalism impacts that might
result from adopting the proposals in this document. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. To
ensure the docket does not contain duplicate comments, commenters
should send only one copy of written comments, or if comments are filed
electronically, commenters should submit only one time.
We will file in the docket all comments that we receive, as well as
a report summarizing each substantive public contact with FAA personnel
concerning this proposed rulemaking. Before acting on this proposal, we
will consider all comments we receive on or before the closing date for
comments. We will consider comments filed after the comment period has
closed if it is possible to do so without incurring expense or delay.
We may change this proposal in light of the comments we receive.

Discussion

We propose to adopt a new AD for Sikorsky Model S-70, S-70A and S-
70C helicopters. Certain parts on Model S-70, S-70A, and S-70C
helicopters are common to military Model UH-60M and SH-60B/F
helicopters. These parts have identical part numbers. However, the part
life limits may be different on the military models and are often lower
due to higher usage and flight load spectrum. This proposed AD is
prompted by the discovery that personnel at a military depot had
installed military Model UH-60M parts on military Model UH-60A/L
helicopters. Because the civilian Model S-70 series helicopters are
derived from the military Model UH-60, it is possible that parts
previously installed on military aircraft with a lower life limit could
inadvertently be later installed on civil aircraft. This proposed AD
would require establishing a pro-rated life limit for each affected
part to account for the heavier usage when previously installed on the
Model UH-60M or SH-60B/F. The proposed actions are intended to
establish appropriate remaining in-service lives to identified parts to
prevent fatigue failure of a part and subsequent loss of control of the
helicopter.

FAA's Determination

We are proposing this AD because we evaluated all known relevant
information and determined that an unsafe condition exists and is
likely to exist or develop on other helicopters of this same type
design.

Proposed AD Requirements

This proposed AD would require, within 25 hours time-in-service,
inserting the component life prorating formula into the airworthiness
limitation section of the maintenance manual or instructions for
continued airworthiness, calculating the new life limit for each part
by applying the formula, and establishing life limits for certain parts
without applying the formula. Furthermore, the proposed AD would
require updating the component log or equivalent record with the new
in-service life limit. This proposed AD would also require replacing
each part that has reached or exceeded its new life limit with an
airworthy part. Lastly, this proposed AD would prohibit installing any
applicable part on a Model S-70, S-70A, or S-70C helicopter if the
number of hours is unknown and would prohibit installing certain parts
on a Model S-70, S-70A, or S-70C helicopter if they have been
previously installed on a Model UH-60M helicopter.

Costs of Compliance

We estimate that this proposed AD would affect 9 helicopters of
U.S. Registry.
We estimate that the cost to insert the pages into the TM would be
negligible.

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

[[Page 44047]]

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, 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 to the extent that
it justifies making a regulatory distinction; 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.
We prepared an economic evaluation of the estimated costs to comply
with this proposed AD and placed it in the AD docket.

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):

Sikorsky Aircraft Corporation (Sikorsky): Docket No. FAA-2013-0636;
Directorate Identifier 2012-SW-065-AD.

(a) Applicability

This AD applies to Model S-70, S-70A, and S-70C helicopters,
certificated in any category, with the following parts installed:
(1) Spindle and liner assembly, part number (P/N) 38023-10374-
041;
(2) Main Rotor Hub, P/N 70070-10046-055 and -056;
(3) Main Rotor Spindle nut, P/N 70102-08105-102;
(4) Main Rotor Control Horn, P/N 70102-08111-047;
(5) Main Rotor Hub, P/N 70103-08112-041 and -047;
(6) Rotating Swashplate, P/N 70104-08001-044 and -045;
(7) Main rotor Shaft Extension, P/N 70351-08186-043;
(8) Main Rotor Gear Box Housing, P/N 70351-38110-043, -044, and
-045;
(9) Main Rotor Shaft, P/N 70351-38131-042;
(10) Output Bevel Gear and Shaft, P/N 70358-06620-101 and -102;
(11) Left Tie Rod Assembly, P/N 70400-08115-043, -045, -046, and
-047;
(12) Forward Bellcrank Support Assembly, P/N 70400-08162-042;
(13) Lateral Servo Bellcrank, P/N 70400-08166-041; or
(14) Tail rotor Servo Assembly, P/N 70410-06520-044 through -
046.

(b) Unsafe Condition

This AD defines the unsafe condition as a critical part
remaining in service beyond its life limit due to previously being
installed on a different helicopter model with higher usage and
flight loads. This condition could result in fatigue failure of a
critical part and subsequent loss of control of the helicopter.

We must receive comments by September 23, 2013.

(d) Compliance

You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

(e) Required Actions

(1) Within 25 hours time-in-service (TIS):
(i) Insert into the airworthiness limitation section of the
maintenance manual or instructions for continued airworthiness the
component life prorating formula in Section 1.1.3 of Sikorsky
Technical Manual TM 1-70-23AW-2, Change 3, dated April 15, 2012.
(ii) Using the service life limits in Table 1 to paragraph (e)
of this AD, apply the component life prorating formula and calculate
the new life limit for each specified part. If the number of hours
of a part is unknown, that part cannot be installed on a Sikorsky
Model S-70, S-70A, or S-70C helicopter. Do not calculate a new life
limit for the part where the Model SH-60 life limit is higher than
the life limit on Models S-70, S-70A, and S-70C.

Table 1 to Paragraph (e)
----------------------------------------------------------------------------------------------------------------
S-70, S-70A, S-
P/N Part description 70C Service UH-60M Service SH-60B/F
life life Service life
----------------------------------------------------------------------------------------------------------------
38023-10374-041....................... Spindle and Liner 8,000 6,400 10,000
Assembly.
70070-10046-055 and -056.............. Main Rotor Hub.......... 5,100 3,100 N/A \1\
70102-08105-102....................... Main Rotor Spindle Nut.. 8,000 6,400 10,000
70102-08111-047....................... Main Rotor Control Horn. 20,000/1,300 10,000 N/A \1\
\2\/2,500 \2\
70103-08112-041 and -047.............. Main Rotor Hub.......... 5,100 3,100 N/A \1\
70104[dash]08001[dash]044[dash]045.... Rotating Swashplate..... 11,000 4,600 9,600
70351-08186-043....................... Main Rotor Shaft 14,000 4,900 16,000
Extension.
70351-38110-043, -044, and -045....... Main Rotor Gear Box 11,000 4,000 9,000
Housing.
70351-38131-042....................... Main Rotor Shaft........ 17,000 5,200 19,000
70358-06620-101 and -102.............. Output Bevel Gear and 5,000 1,800 N/A \1\
Shaft.
70400-08115-043, -045, -046, and Left Tie Rod Assembly... 14,000 4,600 6,300
[dash]047.
70400-08162-042....................... Forward Bellcrank 14,000/2,500 5,600 7,600
Support Assembly. \3\
70400-08166-041....................... Lateral Servo Bellcrank. 20,000 11,000 14,000
70410-06520-044 through -046.......... Tail Rotor Servo 15,000 11,000 N/A \1\
Assembly.
----------------------------------------------------------------------------------------------------------------
\1\ There is no service life limit listed because the parts on Model SH-60B/F have a different P/N than the
parts on Models S-70, S-70A, and S-70C.
\2\ For serial number (S/N) 32479930 through 324791859, with CAGE code 60078, the life limit is 1,300 hours TIS.
For S/N A241-07543 through A241-07594, A241[dash]07706 through A241-07755, A241[dash]07768 through A241-07771,
A241-07800 through A241-07831, R241-00101 through R241-00355, R241-00701 through R241[dash]00966, and R241-
01001 through R241[dash]01166, the life limit is 2,500 hours TIS.
\3\ For S/N A-367-00001 through A367-00035, with CAGE code 78286, the life limit is 2,500 hours TIS.

[[Page 44048]]

(iii) Record the newly-established life limit of each part on
the part's component log card or equivalent record.
(2) After establishing the new life limit, replace each part
that has reached or exceeded its new life limit with an airworthy
part before further flight.
(3) Do not install the following parts on a Model S-70, S-70A,
or S-70C helicopter if they have been previously installed on a
Model UH-60M helicopter:
(i) Bolt, self retaining, P/N 70103-08801-102;
(ii) Bifilar, P/N 70107-08400-046; (iii) Aft Bellcrank, P/N
70400-08102-045;
(iv) Aft Walking Beam Assembly, P/N 70400-08104-048; or
(v) Close Tolerance Bolt, P/N 70400-26802-102 and -103.

(f) Alternative Methods of Compliance (AMOC)

(1) The Manager, Boston Aircraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Davison,
Flight Test Engineer, Boston Aircraft Certification Office, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington,
Massachusetts 01803; telephone (781) 238-7156; email
michael.davison@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office before operating any aircraft
complying with this AD through an AMOC.

(g) Subject

Joint Aircraft Service Component (JASC) Code: 6220 Main Rotor
Hub, 6230 Main Rotor Mast/Swashplate, 6320 Main Rotor Gearbox, 6310
Engine/Transmission Coupling, 6510 Tail Rotor Drive Shaft.

Issued in Fort Worth, Texas, on July 11, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-17629 Filed 7-22-13; 8:45 am]
BILLING CODE 4910-13-P

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