81 FR 27055 - Airworthiness Directives; Bell Helicopter Textron
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 87 (May 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 87 (May 5, 2016)
| Page Range | 27055-27057 | |
| FR Document | 2016-10523 |
[Federal Register Volume 81, Number 87 (Thursday, May 5, 2016)] [Proposed Rules] [Pages 27055-27057] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10523] [[Page 27055]] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede airworthiness directive (AD) 75-26-05 for Bell Helicopter Textron (Bell) Model 204B, 205A-1 and 212 helicopters. AD 75-26-05 currently requires removing and visually inspecting each main rotor (M/R) blade and, depending on the inspection's outcome, repairing or replacing the M/R blades. This proposed AD would require more frequent inspections of certain M/R blades and would also apply to Model 205A helicopters. This proposed AD would have no requirement that helicopter blades be removed to conduct the initial visual inspections. These proposed actions are intended to detect a crack and prevent failure of an M/R blade and subsequent loss of helicopter control. DATES: We must receive comments on this proposed AD by July 5, 2016. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://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 http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3821; 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 rule, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5140; email [email protected]. 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 December 3, 1975, we issued AD 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975) for Bell Model 204B, 205A-1, and 212 helicopters. AD 75-26-05 requires, at intervals not to exceed 12 months installed time, visually inspecting the grip pad, grip plates, doublers, drag plates, and adjacent surfaces for voids, edge voids, corrosion, cracks, and adhesive squeeze-out along bond lines. AD 75-26- 05 prohibits returning to service any blade with a crack or an adhesive void exceeding certain limits. For damage within certain limits, the M/ R blade can be repaired, refinished, and reinstalled. AD 75-26-05 was prompted by an evaluation of a cracked M/R blade that concludes that initial cracking resulted from corrosion. These actions were intended to detect a crack and corrosion and prevent further corrosion in the M/R blade inboard portion. Actions Since AD 75-26-05 Was Issued Since we issued AD 75-26-05, Bell has evaluated an M/R blade installed on a Model UH-1H helicopter with multiple fatigue cracks around the blade retention bolt hole. The cracks resulted from a void between the lower grip plate and the grip pad. A ``substantial'' void also was found at the outboard doubler tip on the lower blade surface. Different part-numbered M/R blades of the same type may also be installed on Model 204B, 205A, and 205A-1 helicopters. We have determined that more frequent inspections than those required by AD 75- 26-05 are necessary to detect cracking or certain damage. While AD 75- 26-05 requires removing the blades from the M/R hub, the inspections in this proposed AD would not. AD 75-26-05 applies to the Model 212 helicopter, and this proposed AD would not because similar inspections on Model 212 blades addressing the unsafe condition are required by AD 2011-23-02 (76 FR 68301, November 4, 2011). We are including specific part-numbered blades in the applicability so that the proposed AD would no longer be required if a new blade is designed that is not subject to the unsafe condition. 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. Related Service Information Bell issued Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013, for the Model UH-1H helicopter (ASB UH-1H-13-09). ASB UH-1H-13-09 specifies a one-time visual inspection, within 10 hours time-in-service (TIS), of the lower grip pad and upper and lower grip plates for cracks, edge voids, and loose or damaged adhesive squeeze- out. ASB UH-1H-13-09 also specifies a repetitive visual inspection, daily and at every 150 [[Page 27056]] hours TIS, of the lower grip pad, upper and lower grip plates, and all upper and the lower doublers for cracks, corrosion, edge voids, and loose or damaged adhesive squeeze-out. Similar inspections are contained in Bell ASB No. 204-75-1 (ASB 204-75-1) and No. 205-75-5 (ASB 205-75-5), both Revision C and both dated April 25, 1979, for Bell Model 204B and 205A-1 helicopters, respectively. ASB 204-75-1 and ASB 205-75-5 call for daily inspections and for inspections, rework, and refinishing every 1,000 hours TIS or 12 months, whichever occurs first. Proposed AD Requirements This proposed AD would require within 25 hours TIS or 2 weeks, whichever occurs first, and thereafter at intervals not to exceed 25 hours TIS or 2 weeks, whichever occurs first, cleaning the upper and lower surfaces of each M/R blade from an area starting at the butt end of the blade to three inches outboard of the doublers. The proposed AD also would require visually inspecting various M/R parts for a crack or corrosion using a 3X or higher power magnifying glass and a light. If there is a crack, corrosion, an edge void, loose or damaged adhesive squeeze-out, or an edge delamination before further flight, this proposed AD would require repairing the M/R blade or replacing it with an airworthy M/R blade, depending on the condition's severity. Differences Between This Proposed AD and the Service Information The proposed AD would require all inspections every 25 hours TIS or 2 weeks, whichever occurs first. ASB UH-1H-13-09 specifies a one-time inspection within 10 hours TIS, and then a second repetitive inspection daily and at every 150 hours TIS, while ASB 204-75-1 and ASB 205-75-5 call for daily visual inspections, and inspections, rework, and refinishing every 1,000 hours TIS or 12 months, whichever occurs first. This proposed AD contains more detailed inspection requirements and a more specific inspection area than the instructions in ASB UH-1H-13-09. The service information applies to M/R blade, part number (P/N) 204- 011-250, and was issued for Model 204B and 205A-1 helicopters. The proposed AD also applies to P/N 204-011-200, because this blade is of the same type and susceptible to the unsafe condition. The proposed AD also applies to certain M/R blades installed on the Model 205A helicopters. While none of these models are registered in the U.S., they were included because of blade P/N eligibility. Costs of Compliance We estimate that this proposed AD would affect 52 helicopters of U.S. Registry and that labor costs average $85 a work-hour. Based on these estimates, we expect the following costs: Cleaning and performing all inspections of a set of M/R blades (2 per helicopter) would require a half work-hour. No parts would be needed. At an estimated 24 inspections a year, the cost would be $1,032 per helicopter and $53,664 for the U.S. fleet. Replacing an M/R blade would require 12 work hours and parts would cost $90,656 for a total cost of $91,676 per blade. 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. 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 removing Airworthiness Directive (AD) No. 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975), and adding the following new AD: Bell Helicopter Textron: Docket No. FAA-2015-3821; Directorate Identifier 2014-SW-025-AD. (a) Applicability This AD applies to Model 204B, 205A, and 205A-1 helicopters with a main rotor (M/R) blade, part number (P/N) 204-011-200-001 or P/N 204-011-250-(all dash numbers), installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in an M/R blade, which could result in failure of an M/R blade and subsequent loss of helicopter control. (c) Affected ADs This AD supersedes AD 75-26-05, Amendment 39-2457 (40 FR 57783, December 12, 1975). (d) Comments Due Date We must receive comments by July 5, 2016. (e) 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. (f) Required Actions (1) Within 25 hours time-in-service (TIS) or 2 weeks, whichever occurs first, and thereafter at intervals not to exceed 25 hours TIS or 2 weeks, whichever occurs first, clean the upper and lower exposed surfaces of each M/R blade from an area starting at the butt end of the blade to three inches outboard of the doublers. Using a 3X or higher power magnifying glass and a light, inspect as follows: [[Page 27057]] (i) Visually inspect the exposed areas of the lower grip pad and upper and lower grip plates of each M/R blade for a crack and any corrosion. (ii) On the upper and lower exposed surfaces of each M/R blade from blade stations 24.5 to 35 for the chord width, visually inspect each layered doubler and blade skin for a crack and any corrosion. Pay particular attention for any cracking in a doubler or skin near or at the same blade station as the blade retention bolt hole (blade station 28). (iii) Visually inspect the exposed areas of each bond line at the edges of the lower grip pad, upper and lower grip plates, and each layered doubler (bond lines) on the upper and lower surfaces of each M/R blade for the entire length and chord width for an edge void, any corrosion, loose or damaged adhesive squeeze-out, and an edge delamination. Pay particular attention to any crack in the paint finish that follows the outline of a grip pad, grip plate, or doubler, and to any loose or damaged adhesive squeeze-out, as these may be the indication of an edge void. (2) If there is a crack, any corrosion, an edge void, loose or damaged adhesive squeeze-out, or an edge delamination during any inspection in paragraph (f)(1) of this AD, before further flight, do the following: (i) If there is a crack in a grip pad or any grip plate or doubler, replace the M/R blade with an airworthy M/R blade. (ii) If there is a crack in the M/R blade skin that is within maximum repair damage limits, repair the M/R blade. If the crack exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/R blade. (iii) If there is any corrosion within maximum repair damage limits, repair the M/R blade. If the corrosion exceeds maximum repair damage limits, replace the M/R blade with an airworthy M/R blade. (iv) If there is an edge void in the grip pad or in a grip plate or doubler, determine the length and depth using a feeler gauge. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (v) If there is an edge void in a grip plate or doubler near the outboard tip, tap inspect the affected area to determine the size and shape of the void. Repair the M/R blade if the edge void is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (vi) If there is any loose or damaged adhesive squeeze-out along any of the bond lines, trim or scrape away the adhesive without damaging the adjacent surfaces or parent material of the M/R blade. Determine if there is an edge void or any corrosion by lightly sanding the trimmed area smooth using 280 or finer grit paper. If there is no edge void or corrosion, refinish the sanded area. (vii) If there is an edge delamination along any of the bond lines or a crack in the paint finish, determine if there is an edge void or a crack in the grip pad, grip plate, doubler, or skin by removing paint from the affected area by lightly sanding in a span- wise direction using 180-220 grit paper. If there are no edge voids and no cracks, refinish the sanded area. (viii) If any parent material is removed during any sanding or trimming in paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD, repair the M/R blade if the damage is within maximum repair damage limits, or replace the M/R blade with an airworthy M/R blade. (g) Special Flight Permit Special flight permits are prohibited. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Fort Worth Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222- 5140; email [email protected]. (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. (i) Additional Information Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013, and ASB No. 204-75-1 and ASB No. 205-75-5, both Revision C and both dated April 25, 1979, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280-3391; fax (817) 280-6466; or at http://www.bellcustomer.com/files/. You may review the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. (j) Subject Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades. Issued in Fort Worth, Texas, on April 15, 2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-10523 Filed 5-4-16; 8:45 am] BILLING CODE 4910-13-P
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hours TIS, of the lower grip pad, upper included because of blade P/N on a substantial number of small entities
and lower grip plates, and all upper and eligibility. under the criteria of the Regulatory
the lower doublers for cracks, corrosion, Flexibility Act.
Costs of Compliance We prepared an economic evaluation
edge voids, and loose or damaged
adhesive squeeze-out. Similar We estimate that this proposed AD of the estimated costs to comply with
inspections are contained in Bell ASB would affect 52 helicopters of U.S. this proposed AD and placed it in the
No. 204–75–1 (ASB 204–75–1) and No. Registry and that labor costs average $85 AD docket.
205–75–5 (ASB 205–75–5), both a work-hour. Based on these estimates,
List of Subjects in 14 CFR Part 39
Revision C and both dated April 25, we expect the following costs:
1979, for Bell Model 204B and 205A–1 Cleaning and performing all Air transportation, Aircraft, Aviation
helicopters, respectively. ASB 204–75–1 inspections of a set of M/R blades (2 per safety, Incorporation by reference,
and ASB 205–75–5 call for daily helicopter) would require a half work- Safety.
inspections and for inspections, rework, hour. No parts would be needed. At an The Proposed Amendment
and refinishing every 1,000 hours TIS or estimated 24 inspections a year, the cost
would be $1,032 per helicopter and Accordingly, under the authority
12 months, whichever occurs first.
$53,664 for the U.S. fleet. delegated to me by the Administrator,
Proposed AD Requirements Replacing an M/R blade would the FAA proposes to amend 14 CFR part
require 12 work hours and parts would 39 as follows:
This proposed AD would require
within 25 hours TIS or 2 weeks, cost $90,656 for a total cost of $91,676
PART 39—AIRWORTHINESS
whichever occurs first, and thereafter at per blade.
DIRECTIVES
intervals not to exceed 25 hours TIS or Authority for This Rulemaking
2 weeks, whichever occurs first, ■ 1. The authority citation for part 39
cleaning the upper and lower surfaces of Title 49 of the United States Code continues to read as follows:
each M/R blade from an area starting at specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, Authority: 49 U.S.C. 106(g), 40113, 44701.
the butt end of the blade to three inches
outboard of the doublers. The proposed section 106, describes the authority of § 39.13 [Amended]
AD also would require visually the FAA Administrator. ‘‘Subtitle VII: ■ 2. The FAA amends § 39.13 by
inspecting various M/R parts for a crack Aviation Programs,’’ describes in more removing Airworthiness Directive (AD)
or corrosion using a 3X or higher power detail the scope of the Agency’s No. 75–26–05, Amendment 39–2457 (40
magnifying glass and a light. authority. FR 57783, December 12, 1975), and
We are issuing this rulemaking under
If there is a crack, corrosion, an edge adding the following new AD:
the authority described in ‘‘Subtitle VII,
void, loose or damaged adhesive Part A, Subpart III, Section 44701: Bell Helicopter Textron: Docket No. FAA–
squeeze-out, or an edge delamination General requirements.’’ Under that 2015–3821; Directorate Identifier 2014–
before further flight, this proposed AD SW–025–AD.
section, Congress charges the FAA with
would require repairing the M/R blade promoting safe flight of civil aircraft in (a) Applicability
or replacing it with an airworthy M/R air commerce by prescribing regulations This AD applies to Model 204B, 205A, and
blade, depending on the condition’s for practices, methods, and procedures 205A–1 helicopters with a main rotor (M/R)
severity. the Administrator finds necessary for blade, part number (P/N) 204–011–200–001
Differences Between This Proposed AD safety in air commerce. This regulation or P/N 204–011–250–(all dash numbers),
is within the scope of that authority installed, certificated in any category.
and the Service Information
because it addresses an unsafe condition (b) Unsafe Condition
The proposed AD would require all that is likely to exist or develop on This AD defines the unsafe condition as a
inspections every 25 hours TIS or 2 products identified in this rulemaking crack in an M/R blade, which could result in
weeks, whichever occurs first. ASB UH– action. failure of an M/R blade and subsequent loss
1H–13–09 specifies a one-time of helicopter control.
inspection within 10 hours TIS, and Regulatory Findings
then a second repetitive inspection (c) Affected ADs
We determined that this proposed AD
daily and at every 150 hours TIS, while would not have federalism implications This AD supersedes AD 75–26–05,
ASB 204–75–1 and ASB 205–75–5 call Amendment 39–2457 (40 FR 57783,
under Executive Order 13132. This December 12, 1975).
for daily visual inspections, and proposed AD would not have a
inspections, rework, and refinishing substantial direct effect on the States, on (d) Comments Due Date
every 1,000 hours TIS or 12 months, the relationship between the national We must receive comments by July 5, 2016.
whichever occurs first. This proposed Government and the States, or on the (e) Compliance
AD contains more detailed inspection distribution of power and
requirements and a more specific You are responsible for performing each
responsibilities among the various action required by this AD within the
inspection area than the instructions in levels of government. specified compliance time unless it has
ASB UH–1H–13–09. The service For the reasons discussed, I certify already been accomplished prior to that time.
information applies to M/R blade, part this proposed regulation:
number (P/N) 204–011–250, and was 1. Is not a ‘‘significant regulatory (f) Required Actions
issued for Model 204B and 205A–1 action’’ under Executive Order 12866; (1) Within 25 hours time-in-service (TIS) or
helicopters. The proposed AD also 2 weeks, whichever occurs first, and
ehiers on DSK5VPTVN1PROD with PROPOSALS
2. Is not a ‘‘significant rule’’ under the
applies to P/N 204–011–200, because DOT Regulatory Policies and Procedures thereafter at intervals not to exceed 25 hours
this blade is of the same type and TIS or 2 weeks, whichever occurs first, clean
(44 FR 11034, February 26, 1979);
the upper and lower exposed surfaces of each
susceptible to the unsafe condition. The 3. Will not affect intrastate aviation in M/R blade from an area starting at the butt
proposed AD also applies to certain Alaska to the extent that it justifies end of the blade to three inches outboard of
M/R blades installed on the Model 205A making a regulatory distinction; and the doublers. Using a 3X or higher power
helicopters. While none of these models 4. Will not have a significant magnifying glass and a light, inspect as
are registered in the U.S., they were economic impact, positive or negative, follows:
VerDate Sep<11>2014 14:43 May 04, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\05MYP1.SGM 05MYP1](https://thefederalregister.org/doc/81_FR_27142/page/2.svg)
![Federal Register / Vol. 81, No. 87 / Thursday, May 5, 2016 / Proposed Rules 27057
(i) Visually inspect the exposed areas of the are no edge voids and no cracks, refinish the DEPARTMENT OF TRANSPORTATION
lower grip pad and upper and lower grip sanded area.
plates of each M/R blade for a crack and any (viii) If any parent material is removed Federal Aviation Administration
corrosion. during any sanding or trimming in
(ii) On the upper and lower exposed paragraphs (f)(2)(vi) or (f)(2)(vii) of this AD,
surfaces of each M/R blade from blade
14 CFR Part 39
repair the M/R blade if the damage is within
stations 24.5 to 35 for the chord width, [Docket No. FAA–2015–3941; Directorate
visually inspect each layered doubler and maximum repair damage limits, or replace
Identifier 2015–SW–052–AD]
blade skin for a crack and any corrosion. Pay the M/R blade with an airworthy M/R blade.
particular attention for any cracking in a RIN 2120–AA64
(g) Special Flight Permit
doubler or skin near or at the same blade
station as the blade retention bolt hole (blade Special flight permits are prohibited. Airworthiness Directives; Airbus
station 28). Helicopters Deutschland GmbH
(h) Alternative Methods of Compliance
(iii) Visually inspect the exposed areas of Helicopters
(AMOCs)
each bond line at the edges of the lower grip
pad, upper and lower grip plates, and each (1) The Manager, Fort Worth Aircraft AGENCY: Federal Aviation
layered doubler (bond lines) on the upper Certification Office, FAA, may approve Administration (FAA), DOT.
and lower surfaces of each M/R blade for the AMOCs for this AD. Send your proposal to: ACTION: Notice of proposed rulemaking
entire length and chord width for an edge Charles Harrison, Project Manager, Fort (NPRM).
void, any corrosion, loose or damaged Worth Aircraft Certification Office, FAA,
adhesive squeeze-out, and an edge SUMMARY: We propose to adopt a new
10101 Hillwood Pkwy, Fort Worth, TX
delamination. Pay particular attention to any airworthiness directive (AD) for Airbus
crack in the paint finish that follows the 76177; telephone (817) 222–5140; email 7-
outline of a grip pad, grip plate, or doubler, AVS-ASW-170@faa.gov. Helicopters Deutschland GmbH (Airbus
and to any loose or damaged adhesive (2) For operations conducted under a 14 Helicopters) Model MBB–BK 117A–3,
squeeze-out, as these may be the indication CFR part 119 operating certificate or under MBB–BK 117A–4, MBB–BK 117B–1,
of an edge void. 14 CFR part 91, subpart K, we suggest that MBB–BK 117B–2, and MBB–BK 117C–
(2) If there is a crack, any corrosion, an you notify your principal inspector, or 1 helicopters. This proposed AD would
edge void, loose or damaged adhesive lacking a principal inspector, the manager of require removing adhesive seals from
squeeze-out, or an edge delamination during the local flight standards district office or the exterior and interior door jettisoning
any inspection in paragraph (f)(1) of this AD, certificate holding district office before system on the left and right sliding
before further flight, do the following: operating any aircraft complying with this doors. This proposed AD is prompted
(i) If there is a crack in a grip pad or any
AD through an AMOC. by reports that the adhesive seal
grip plate or doubler, replace the M/R blade
with an airworthy M/R blade. (i) Additional Information
prevented the doors from jettisoning
(ii) If there is a crack in the M/R blade skin properly. The proposed actions are
Bell Helicopter Alert Service Bulletin intended to remove the adhesive seal to
that is within maximum repair damage
limits, repair the M/R blade. If the crack (ASB) No. UH–1H–13–09, dated January 14, allow the doors to jettison properly so
exceeds maximum repair damage limits, 2013, and ASB No. 204–75–1 and ASB No. occupants can exit the helicopter during
replace the M/R blade with an airworthy M/ 205–75–5, both Revision C and both dated an emergency.
R blade. April 25, 1979, which are not incorporated
DATES: We must receive comments on
(iii) If there is any corrosion within by reference, contain additional information
maximum repair damage limits, repair the M/ about the subject of this AD. For service this proposed AD by July 5, 2016.
R blade. If the corrosion exceeds maximum information identified in this AD, contact ADDRESSES: You may send comments by
repair damage limits, replace the M/R blade Bell Helicopter Textron, Inc., P.O. Box 482, any of the following methods:
with an airworthy M/R blade. Fort Worth, TX 76101; telephone (817) 280– • Federal eRulemaking Docket: Go to
(iv) If there is an edge void in the grip pad 3391; fax (817) 280–6466; or at http:// http://www.regulations.gov. Follow the
or in a grip plate or doubler, determine the online instructions for sending your
www.bellcustomer.com/files/. You may
length and depth using a feeler gauge. Repair
review the service information at the FAA, comments electronically.
the M/R blade if the edge void is within
maximum repair damage limits, or replace Office of the Regional Counsel, Southwest • Fax: 202–493–2251.
the M/R blade with an airworthy M/R blade. Region, 10101 Hillwood Pkwy, Room 6N– • Mail: Send comments to the U.S.
(v) If there is an edge void in a grip plate 321, Fort Worth, TX 76177. Department of Transportation, Docket
or doubler near the outboard tip, tap inspect Operations, M–30, West Building
(j) Subject
the affected area to determine the size and Ground Floor, Room W12–140, 1200
shape of the void. Repair the M/R blade if the Joint Aircraft Service Component (JASC) New Jersey Avenue SE., Washington,
edge void is within maximum repair damage Code: 6210, Main Rotor Blades. DC 20590–0001.
limits, or replace the M/R blade with an • Hand Delivery: Deliver to the
Issued in Fort Worth, Texas, on April 15,
airworthy M/R blade.
2016. ‘‘Mail’’ address between 9 a.m. and 5
(vi) If there is any loose or damaged
adhesive squeeze-out along any of the bond Scott A. Horn, p.m., Monday through Friday, except
lines, trim or scrape away the adhesive Federal holidays.
Acting Manager, Rotorcraft Directorate,
without damaging the adjacent surfaces or Aircraft Certification Service. Examining the AD Docket
parent material of the M/R blade. Determine
[FR Doc. 2016–10523 Filed 5–4–16; 8:45 am] You may examine the AD docket on
if there is an edge void or any corrosion by
lightly sanding the trimmed area smooth BILLING CODE 4910–13–P the Internet at http://
using 280 or finer grit paper. If there is no www.regulations.gov by searching for
edge void or corrosion, refinish the sanded and locating Docket No. FAA–2015–
ehiers on DSK5VPTVN1PROD with PROPOSALS
area. 3941; or in person at the Docket
(vii) If there is an edge delamination along
Operations Office between 9 a.m. and 5
any of the bond lines or a crack in the paint
finish, determine if there is an edge void or p.m., Monday through Friday, except
a crack in the grip pad, grip plate, doubler, Federal holidays. The AD docket
or skin by removing paint from the affected contains this proposed AD, the
area by lightly sanding in a span-wise European Aviation Safety Agency
direction using 180–220 grit paper. If there (EASA) AD, the economic evaluation,
VerDate Sep<11>2014 14:43 May 04, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\05MYP1.SGM 05MYP1](https://thefederalregister.org/doc/81_FR_27142/page/3.svg)
Document Created: 2016-05-05 01:15:04
Document Modified: 2016-05-05 01:15:04
| 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 5, 2016. | |
| Contact | Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5140; email [email protected] | |
| FR Citation | 81 FR 27055 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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