83 FR 2358 - Airworthiness Directives; Bell Helicopter Textron Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 11 (January 17, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 11 (January 17, 2018)
| Page Range | 2358-2360 | |
| FR Document | 2018-00660 |
[Federal Register Volume 83, Number 11 (Wednesday, January 17, 2018)] [Rules and Regulations] [Pages 2358-2360] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-00660] [[Page 2358]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0895; Product Identifier 2017-SW-048-AD; Amendment 39-19161; AD 2018-02-08] RIN 2120-AA64 Airworthiness Directives; Bell Helicopter Textron Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (Bell) Model 204B, 205A, and 205A-1 helicopters with a Helicopter Technology Company (HTC) main rotor (M/R) blade installed. This AD requires cleaning and visually inspecting the M/R blades, and depending on the outcome of the inspection, repairing or replacing the M/R blades. This AD is prompted by a report of an M/R blade with a fatigue crack in the grip plate and doublers at the blade retention bolt hole. The actions of this AD are intended to correct an unsafe condition on these products. DATES: This AD becomes effective February 1, 2018. We must receive comments on this AD by March 19, 2018. 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-2017- 0895; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, any comments received, and other information. The street address for Docket Operations (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 final 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 the referenced 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: Galib Abumeri, Aerospace Engineer (Structures), Airframe Section, Los Angeles ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone 562-627-5324; email galib.abumeri@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, 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 resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, 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 them 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 rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion We are adopting a new AD for Bell 204B, 205A and 205A-1 helicopters with an HTC M/R blade part number (P/N) 204P2100-101 installed. This AD requires repetitive inspections of the exposed areas of the lower grip pad and upper and lower grip plates of each M/R blade for a crack, corrosion, an edge void, loose or damaged adhesive squeeze-out, and an edge delamination. The actions of this AD are the same as those required by AD 2016- 22-07 (81 FR 74285, October 26, 2016), which applies to Bell Model 204B, 205A and 205A-1 helicopters with an M/R blade P/N 204-011-200-001 or P/N 204-011-250-(all dash numbers) installed. AD 2016-22-07 was prompted by a report of an M/R blade with multiple fatigue cracks around the retention bolt hole. This AD is prompted by a report that during a ground inspection, a crack was discovered in the grip plate and doublers at the blade retention bolt hole of a UH-1B helicopter model. The blade, which HTC produced for restricted category and commercial model helicopters, had 926 hours TIS and is of the same design as the M/R blades in AD 2016- 22-07. We are issuing this AD to detect or prevent a crack, which could lead to failure of an M/R blade and subsequent loss of helicopter control. FAA's Determination We are issuing 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 HTC has issued Service Notice No. 204-2100-1 on July 5, 2017, for affected helicopters with M/R blade P/N 204P2100-101, serial numbers A099 through A119 installed. This service notice specifies cleaning and visually inspecting the M/R blades and depending on the outcome, repairing or replacing the blades in accordance with AD 2016-23-09. We also reviewed Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013, for the Model UH-1H helicopter. ASB No. 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 No. UH-1H-13-09 also specifies a repetitive and more detailed visual inspection, daily and at every 150 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. Lastly, we reviewed Bell Helicopter ASB No. 204-75-1 for Model 204B helicopters and ASB No. 205-75-5 for Model 205A-1 helicopters, both Revision C and both dated April 25, 1979. ASB No. 204-75-1 and ASB No. 205-75-5 specify visually inspecting [[Page 2359]] the M/R blades during each daily inspection. ASB No. 204-75-1 and ASB No. 205-75-5 also provide instructions for repetitively inspecting the blades every 1,000 hours of operation or every 12 months, whichever occurs first. AD Requirements This AD requires 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, cleaning 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, this AD also requires visually inspecting various M/R blade parts for a crack or corrosion. If there is a crack, corrosion, an edge void, loose or damaged adhesive squeeze-out, or an edge delamination, before further flight, this AD requires repairing the M/R blade or replacing it with an airworthy M/R blade, depending on whether the condition is within maximum repair damage limits. This AD also requires reporting information about any cracks found during the inspection to the FAA within 10 days. Differences Between This AD and the Service Information This AD requires all inspections every 25 hours TIS or 2 weeks, whichever occurs first. 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. The service information applies to Bell M/R blade P/N 204-011-250. This AD applies to HTC M/R blade P/N 204P2100-101. Interim Action We consider this AD to be an interim action. The notification of a crack in the M/R blade that is required by this AD may enable us to obtain better insight into the cause of the M/R blade cracking. This information may help us develop additional action to address this unsafe condition. Once this action is developed, approved, and available, we might consider additional rulemaking. Costs of Compliance We estimate that this AD affects 10 helicopters of U.S. Registry and that labor costs average $85 per 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) requires 0.5 work-hour for a cost of $43 per helicopter and $430 for the U.S. fleet per inspection cycle. Replacing an M/R blade requires 12 work-hours and parts cost $86,000 for a total cost of $87,020 per blade. Reporting the inspection results required by this AD will require about 0.5 work-hour for a cost of $43 per helicopter and $430 for the U.S. fleet per report. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting required by this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES-200. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the required corrective actions must be accomplished within two weeks. Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for prior public comment before issuing this AD are impracticable and that good cause exists to make this AD effective in less than 30 days. 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under 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 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): 2018-02-08 Bell Helicopter Textron: Amendment 39-19161; Docket No. [[Page 2360]] FAA-2017-0895; Product Identifier 2017-SW-048-AD. (a) Applicability This AD applies to Bell Helicopter Textron (Bell) Model 204B, 205A, and 205A-1 helicopters with a Helicopter Technology Company (HTC) main rotor (M/R) blade part number 204P2100-101 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) Effective Date This AD becomes effective February 1, 2018. (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) 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: (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 (e)(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 (e)(2)(vi) or (e)(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. (3) If there is a crack during any inspection in paragraph (e)(1) of this AD, within 10 days after completing the inspection, report the information requested in Appendix 1 to this AD by mail to the Los Angeles ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712; attn. Galib Abumeri; or by email to galib.abumeri@faa.gov. (f) Special Flight Permits Special flight permits are prohibited. (g) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 30 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Galib Abumeri, Aerospace Engineer (Structures), Airframe Section, Los Angeles ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone 562-627-5324; email galib.abumeri@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. (i) Additional Information HTC Service Notice No. 204-2100-1, dated July 5, 2017; Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013; Bell ASB No. 204-75-1 and Bell 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 this 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 January 9, 2018. James A. Grigg, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. Appendix 1 to AD 2018-02-08 Please report the following information by mail to the Los Angeles ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712; attn. Galib Abumeri; or by email to galib.abumeri@faa.gov. (1) Date of inspection: (2) Aircraft N-number: (3) M/R blade serial number: (4) M/R blade hours of time-in-service: (5) Location of each crack: (6) Dimension of each crack: (7) Primary operating location of the M/R blade: [FR Doc. 2018-00660 Filed 1-16-18; 8:45 am] BILLING CODE 4910-13-P
![2358 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION street address for Docket Operations The actions of this AD are the same
(telephone 800–647–5527) is in the as those required by AD 2016–22–07 (81
Federal Aviation Administration ADDRESSES section. Comments will be FR 74285, October 26, 2016), which
available in the AD docket shortly after applies to Bell Model 204B, 205A and
14 CFR Part 39 receipt. 205A–1 helicopters with an M/R blade
[Docket No. FAA–2017–0895; Product For service information identified in P/N 204–011–200–001 or P/N 204–011–
Identifier 2017–SW–048–AD; Amendment this final rule, contact Bell Helicopter 250-(all dash numbers) installed. AD
39–19161; AD 2018–02–08] Textron, Inc., P.O. Box 482, Fort Worth, 2016–22–07 was prompted by a report
TX 76101; telephone (817) 280–3391; of an M/R blade with multiple fatigue
RIN 2120–AA64 cracks around the retention bolt hole.
fax (817) 280–6466; or at http://
www.bellcustomer.com/files/. You may This AD is prompted by a report that
Airworthiness Directives; Bell during a ground inspection, a crack was
Helicopter Textron Helicopters review the referenced service
information at the FAA, Office of the discovered in the grip plate and
AGENCY: Federal Aviation Regional Counsel, Southwest Region, doublers at the blade retention bolt hole
Administration (FAA), DOT. 10101 Hillwood Pkwy, Room 6N–321, of a UH–1B helicopter model. The
ACTION: Final rule; request for Fort Worth, TX 76177. blade, which HTC produced for
comments. FOR FURTHER INFORMATION CONTACT:
restricted category and commercial
Galib Abumeri, Aerospace Engineer model helicopters, had 926 hours TIS
SUMMARY: We are adopting a new (Structures), Airframe Section, Los and is of the same design as the M/R
airworthiness directive (AD) for Bell Angeles ACO Branch, Compliance and blades in AD 2016–22–07. We are
Helicopter Textron (Bell) Model 204B, Airworthiness Division, FAA, 3960 issuing this AD to detect or prevent a
205A, and 205A–1 helicopters with a Paramount Blvd., Lakewood, California crack, which could lead to failure of an
Helicopter Technology Company (HTC) 90712; telephone 562–627–5324; email M/R blade and subsequent loss of
main rotor (M/R) blade installed. This galib.abumeri@faa.gov. helicopter control.
AD requires cleaning and visually FAA’s Determination
SUPPLEMENTARY INFORMATION:
inspecting the M/R blades, and
depending on the outcome of the Comments Invited We are issuing this AD because we
inspection, repairing or replacing the M/ evaluated all the relevant information
This AD is a final rule that involves and determined the unsafe condition
R blades. This AD is prompted by a
requirements affecting flight safety, and described previously is likely to exist or
report of an M/R blade with a fatigue
we did not provide you with notice and develop in other products of these same
crack in the grip plate and doublers at
an opportunity to provide your type designs.
the blade retention bolt hole. The
comments prior to it becoming effective.
actions of this AD are intended to Related Service Information
However, we invite you to participate in
correct an unsafe condition on these
this rulemaking by submitting written HTC has issued Service Notice No.
products.
comments, data, or views. We also 204–2100–1 on July 5, 2017, for affected
DATES: This AD becomes effective invite comments relating to the helicopters with M/R blade P/N
February 1, 2018. economic, environmental, energy, or 204P2100–101, serial numbers A099
We must receive comments on this federalism impacts that resulted from through A119 installed. This service
AD by March 19, 2018. adopting this AD. The most helpful notice specifies cleaning and visually
ADDRESSES: You may send comments by comments reference a specific portion of inspecting the M/R blades and
any of the following methods: the AD, explain the reason for any depending on the outcome, repairing or
• Federal eRulemaking Docket: Go to recommended change, and include replacing the blades in accordance with
http://www.regulations.gov. Follow the supporting data. To ensure the docket AD 2016–23–09.
online instructions for sending your does not contain duplicate comments, We also reviewed Bell Helicopter
comments electronically. commenters should send only one copy Alert Service Bulletin (ASB) No. UH–
• Fax: 202–493–2251. of written comments, or if comments are 1H–13–09, dated January 14, 2013, for
• Mail: Send comments to the U.S. filed electronically, commenters should the Model UH–1H helicopter. ASB No.
Department of Transportation, Docket submit them only one time. We will file UH–1H–13–09 specifies a one-time
Operations, M–30, West Building in the docket all comments that we visual inspection, within 10 hours time-
Ground Floor, Room W12–140, 1200 receive, as well as a report summarizing in-service (TIS), of the lower grip pad
New Jersey Avenue SE, Washington, DC each substantive public contact with and upper and lower grip plates for
20590–0001. FAA personnel concerning this cracks, edge voids, and loose or
• Hand Delivery: Deliver to the rulemaking during the comment period. damaged adhesive squeeze-out. ASB No.
‘‘Mail’’ address between 9 a.m. and 5 We will consider all the comments we UH–1H–13–09 also specifies a repetitive
p.m., Monday through Friday, except receive and may conduct additional and more detailed visual inspection,
Federal holidays. rulemaking based on those comments. daily and at every 150 hours TIS, of the
lower grip pad, upper and lower grip
Examining the AD Docket Discussion
plates, and all upper and the lower
You may examine the AD docket on We are adopting a new AD for Bell doublers for cracks, corrosion, edge
the internet at http:// 204B, 205A and 205A–1 helicopters voids, and loose or damaged adhesive
www.regulations.gov by searching for with an HTC M/R blade part number (P/ squeeze-out.
and locating Docket No. FAA–2017– N) 204P2100–101 installed. This AD Lastly, we reviewed Bell Helicopter
ethrower on DSK3G9T082PROD with RULES
0895; or in person at Docket Operations requires repetitive inspections of the ASB No. 204–75–1 for Model 204B
between 9 a.m. and 5 p.m., Monday exposed areas of the lower grip pad and helicopters and ASB No. 205–75–5 for
through Friday, except Federal holidays. upper and lower grip plates of each M/ Model 205A–1 helicopters, both
The AD docket contains this AD, the R blade for a crack, corrosion, an edge Revision C and both dated April 25,
economic evaluation, any comments void, loose or damaged adhesive 1979. ASB No. 204–75–1 and ASB No.
received, and other information. The squeeze-out, and an edge delamination. 205–75–5 specify visually inspecting
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![Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations 2359
the M/R blades during each daily helicopter) requires 0.5 work-hour for a We are issuing this rulemaking under
inspection. ASB No. 204–75–1 and ASB cost of $43 per helicopter and $430 for the authority described in ‘‘Subtitle VII,
No. 205–75–5 also provide instructions the U.S. fleet per inspection cycle. Part A, Subpart III, Section 44701:
for repetitively inspecting the blades • Replacing an M/R blade requires 12 General requirements.’’ Under that
every 1,000 hours of operation or every work-hours and parts cost $86,000 for a section, Congress charges the FAA with
12 months, whichever occurs first. total cost of $87,020 per blade. promoting safe flight of civil aircraft in
• Reporting the inspection results air commerce by prescribing regulations
AD Requirements required by this AD will require about for practices, methods, and procedures
This AD requires within 25 hours 0.5 work-hour for a cost of $43 per the Administrator finds necessary for
time-in-service (TIS) or 2 weeks, helicopter and $430 for the U.S. fleet safety in air commerce. This regulation
whichever occurs first, and thereafter at per report. is within the scope of that authority
intervals not to exceed 25 hours TIS or because it addresses an unsafe condition
Paperwork Reduction Act
2 weeks, whichever occurs first, that is likely to exist or develop on
cleaning the upper and lower exposed A federal agency may not conduct or products identified in this rulemaking
surfaces of each M/R blade from an area sponsor, and a person is not required to action.
starting at the butt end of the blade to respond to, nor shall a person be subject
three inches outboard of the doublers. to penalty for failure to comply with a Regulatory Findings
Using a 3X or higher power magnifying collection of information subject to the We determined that this AD will not
glass and a light, this AD also requires requirements of the Paperwork have federalism implications under
visually inspecting various M/R blade Reduction Act unless that collection of Executive Order 13132. This AD will
parts for a crack or corrosion. If there is information displays a current valid not have a substantial direct effect on
a crack, corrosion, an edge void, loose OMB control number. The control the States, on the relationship between
or damaged adhesive squeeze-out, or an number for the collection of information the national Government and the States,
edge delamination, before further flight, required by this AD is 2120–0056. The or on the distribution of power and
this AD requires repairing the M/R paperwork cost associated with this AD responsibilities among the various
blade or replacing it with an airworthy has been detailed in the Costs of levels of government.
M/R blade, depending on whether the Compliance section of this document For the reasons discussed, I certify
condition is within maximum repair and includes time for reviewing that this AD:
damage limits. instructions, as well as completing and 1. Is not a ‘‘significant regulatory
This AD also requires reporting reviewing the collection of information. action’’ under Executive Order 12866;
information about any cracks found Therefore, all reporting required by this 2. Is not a ‘‘significant rule’’ under
during the inspection to the FAA within AD is mandatory. Comments concerning DOT Regulatory Policies and Procedures
10 days. the accuracy of this burden and (44 FR 11034, February 26, 1979);
suggestions for reducing the burden 3. Will not affect intrastate aviation in
Differences Between This AD and the should be directed to the FAA at 800 Alaska to the extent that it justifies
Service Information Independence Ave. SW, Washington, making a regulatory distinction; and
This AD requires all inspections every DC 20591. ATTN: Information 4. Will not have a significant
25 hours TIS or 2 weeks, whichever Collection Clearance Officer, AES–200. economic impact, positive or negative,
occurs first. ASB 204–75–1 and ASB on a substantial number of small entities
FAA’s Justification and Determination under the criteria of the Regulatory
205–75–5 call for daily visual
of the Effective Date Flexibility Act.
inspections, and inspections, rework,
and refinishing every 1,000 hours TIS or Providing an opportunity for public We prepared an economic evaluation
12 months, whichever occurs first. The comments prior to adopting these AD of the estimated costs to comply with
service information applies to Bell M/R requirements would delay this AD and placed it in the AD docket.
blade P/N 204–011–250. This AD implementing the safety actions needed
List of Subjects in 14 CFR Part 39
applies to HTC M/R blade P/N to correct this known unsafe condition.
204P2100–101. Therefore, we find that the risk to the Air transportation, Aircraft, Aviation
flying public justifies waiving notice safety, Incorporation by reference,
Interim Action and comment prior to the adoption of Safety.
We consider this AD to be an interim this rule because the required corrective Adoption of the Amendment
action. The notification of a crack in the actions must be accomplished within
M/R blade that is required by this AD two weeks. Accordingly, under the authority
may enable us to obtain better insight Since an unsafe condition exists that delegated to me by the Administrator,
into the cause of the M/R blade requires the immediate adoption of this the FAA amends 14 CFR part 39 as
cracking. This information may help us AD, we determined that notice and follows:
develop additional action to address opportunity for prior public comment
this unsafe condition. Once this action before issuing this AD are impracticable PART 39—AIRWORTHINESS
is developed, approved, and available, and that good cause exists to make this DIRECTIVES
we might consider additional AD effective in less than 30 days. ■ 1. The authority citation for part 39
rulemaking. continues to read as follows:
Authority for This Rulemaking
Costs of Compliance Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701.
specifies the FAA’s authority to issue
ethrower on DSK3G9T082PROD with RULES
We estimate that this AD affects 10 § 39.13 [Amended]
helicopters of U.S. Registry and that rules on aviation safety. Subtitle I,
labor costs average $85 per work-hour. section 106, describes the authority of ■ 2. The FAA amends § 39.13 by adding
Based on these estimates, we expect the the FAA Administrator. ‘‘Subtitle VII: the following new airworthiness
following costs: Aviation Programs,’’ describes in more directive (AD):
• Cleaning and performing all detail the scope of the Agency’s 2018–02–08 Bell Helicopter Textron:
inspections of a set of M/R blades (2 per authority. Amendment 39–19161; Docket No.
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![2360 Federal Register / Vol. 83, No. 11 / Wednesday, January 17, 2018 / Rules and Regulations
FAA–2017–0895; Product Identifier replace the M/R blade with an airworthy M/ are mandatory. Comments concerning the
2017–SW–048–AD. R blade. accuracy of this burden and suggestions for
(iii) If there is any corrosion within reducing the burden should be directed to
(a) Applicability maximum repair damage limits, repair the M/ the FAA at: 800 Independence Ave. SW,
This AD applies to Bell Helicopter Textron R blade. If the corrosion exceeds maximum Washington, DC 20591, Attn: Information
(Bell) Model 204B, 205A, and 205A–1 repair damage limits, replace the M/R blade Collection Clearance Officer, AES–200.
helicopters with a Helicopter Technology with an airworthy M/R blade.
Company (HTC) main rotor (M/R) blade part (iv) If there is an edge void in the grip pad (h) Alternative Methods of Compliance
number 204P2100–101 installed, certificated or in a grip plate or doubler, determine the (AMOCs)
in any category. length and depth using a feeler gauge. Repair (1) The Manager, Los Angeles ACO Branch,
(b) Unsafe Condition the M/R blade if the edge void is within FAA, may approve AMOCs for this AD. Send
maximum repair damage limits or replace the your proposal to: Galib Abumeri, Aerospace
This AD defines the unsafe condition as a M/R blade with an airworthy M/R blade. Engineer (Structures), Airframe Section, Los
crack in an M/R blade, which could result in (v) If there is an edge void in a grip plate Angeles ACO Branch, Compliance and
failure of an M/R blade and subsequent loss or doubler near the outboard tip, tap inspect Airworthiness Division, FAA, 3960
of helicopter control. the affected area to determine the size and Paramount Blvd., Lakewood, California
(c) Effective Date shape of the void. Repair the M/R blade if the 90712; telephone 562–627–5324; email
edge void is within maximum repair damage galib.abumeri@faa.gov.
This AD becomes effective February 1,
limits or replace the M/R blade with an (2) For operations conducted under a 14
2018.
airworthy M/R blade. CFR part 119 operating certificate or under
(d) Compliance (vi) If there is any loose or damaged 14 CFR part 91, subpart K, we suggest that
You are responsible for performing each adhesive squeeze-out along any of the bond you notify your principal inspector, or
action required by this AD within the lines, trim or scrape away the adhesive lacking a principal inspector, the manager of
specified compliance time unless it has without damaging the adjacent surfaces or the local flight standards district office or
already been accomplished prior to that time. parent material of the M/R blade. Determine certificate holding district office before
if there is an edge void or any corrosion by operating any aircraft complying with this
(e) Required Actions lightly sanding the trimmed area smooth AD through an AMOC.
(1) Within 25 hours time-in-service (TIS) or using 280 or finer grit paper. If there is no
2 weeks, whichever occurs first, and edge void or corrosion, refinish the sanded (i) Additional Information
thereafter at intervals not to exceed 25 hours area. HTC Service Notice No. 204–2100–1, dated
TIS or 2 weeks, whichever occurs first, clean (vii) If there is an edge delamination along July 5, 2017; Alert Service Bulletin (ASB) No.
the upper and lower exposed surfaces of each any of the bond lines or a crack in the paint UH–1H–13–09, dated January 14, 2013; Bell
M/R blade from an area starting at the butt finish, determine if there is an edge void or ASB No. 204–75–1 and Bell ASB No. 205–
end of the blade to three inches outboard of a crack in the grip pad, grip plate, doubler, 75–5, both Revision C and both dated April
the doublers. Using a 3X or higher power or skin by removing paint from the affected 25, 1979, which are not incorporated by
magnifying glass and a light, inspect as area by lightly sanding in a span-wise reference, contain additional information
follows: direction using 180–220 grit paper. If there about the subject of this AD. For service
(i) Visually inspect the exposed areas of the are no edge voids and no cracks, refinish the information identified in this AD, contact
lower grip pad and upper and lower grip sanded area. Bell Helicopter Textron, Inc., P.O. Box 482,
plates of each M/R blade for a crack and any (viii) If any parent material is removed
Fort Worth, TX 76101; telephone (817) 280–
corrosion. during any sanding or trimming in
3391; fax (817) 280–6466; or at http://
(ii) On the upper and lower exposed paragraphs (e)(2)(vi) or (e)(2)(vii) of this AD,
www.bellcustomer.com/files/. You may
surfaces of each M/R blade from blade repair the M/R blade if the damage is within
review this service information at the FAA,
stations 24.5 to 35 for the chord width, maximum repair damage limits or replace the
Office of the Regional Counsel, Southwest
visually inspect each layered doubler and M/R blade with an airworthy M/R blade.
Region, 10101 Hillwood Pkwy., Room 6N–
blade skin for a crack and any corrosion. Pay (3) If there is a crack during any inspection
321, Fort Worth, TX 76177.
particular attention for any cracking in a in paragraph (e)(1) of this AD, within 10 days
doubler or skin near or at the same blade after completing the inspection, report the (j) Subject
station as the blade retention bolt hole (blade information requested in Appendix 1 to this Joint Aircraft Service Component (JASC)
station 28). AD by mail to the Los Angeles ACO Branch, Code: 6210, Main Rotor Blades.
(iii) Visually inspect the exposed areas of Compliance and Airworthiness Division,
each bond line at the edges of the lower grip FAA, 3960 Paramount Blvd., Lakewood, Issued in Fort Worth, Texas, on January 9,
pad, upper and lower grip plates, and each California 90712; attn. Galib Abumeri; or by 2018.
layered doubler (bond lines) on the upper email to galib.abumeri@faa.gov.
and lower surfaces of each M/R blade for the James A. Grigg,
entire length and chord width for an edge (f) Special Flight Permits Acting Director, Compliance & Airworthiness
void, any corrosion, loose or damaged Special flight permits are prohibited. Division, Aircraft Certification Service.
adhesive squeeze-out, and an edge
delamination. Pay particular attention to any (g) Paperwork Reduction Act Burden Appendix 1 to AD 2018–02–08
crack in the paint finish that follows the Statement
Please report the following information by
outline of a grip pad, grip plate, or doubler, A federal agency may not conduct or mail to the Los Angeles ACO Branch,
and to any loose or damaged adhesive sponsor, and a person is not required to Compliance and Airworthiness Division,
squeeze-out, as these may be the indication respond to, nor shall a person be subject to FAA, 3960 Paramount Blvd., Lakewood,
of an edge void. a penalty for failure to comply with a California 90712; attn. Galib Abumeri; or by
(2) If there is a crack, any corrosion, an collection of information subject to the email to galib.abumeri@faa.gov.
edge void, loose or damaged adhesive requirements of the Paperwork Reduction (1) Date of inspection:
squeeze-out, or an edge delamination during Act unless that collection of information (2) Aircraft N-number:
any inspection in paragraph (e)(1) of this AD, displays a current valid OMB Control (3) M/R blade serial number:
before further flight, do the following: Number. The OMB Control Number for this
ethrower on DSK3G9T082PROD with RULES
(4) M/R blade hours of time-in-service:
(i) If there is a crack in a grip pad or any information collection is 2120–0056. Public (5) Location of each crack:
grip plate or doubler, replace the M/R blade reporting for this collection of information is (6) Dimension of each crack:
with an airworthy M/R blade. estimated to be approximately 30 minutes (7) Primary operating location of the M/R
(ii) If there is a crack in the M/R blade skin per response, including the time for
blade:
that is within maximum repair damage reviewing instructions, completing and
limits, repair the M/R blade. If the crack reviewing the collection of information. All [FR Doc. 2018–00660 Filed 1–16–18; 8:45 am]
exceeds maximum repair damage limits, responses to this collection of information BILLING CODE 4910–13–P
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Document Created: 2018-10-26 09:55:06
Document Modified: 2018-10-26 09:55:06
| 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 | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective February 1, 2018. | |
| Contact | Galib Abumeri, Aerospace Engineer (Structures), Airframe Section, Los Angeles ACO Branch, Compliance and Airworthiness Division, FAA, 3960 Paramount Blvd., Lakewood, California 90712; telephone 562-627-5324; email [email protected] | |
| FR Citation | 83 FR 2358 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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