81 FR 83660 - Airworthiness Directives; Various Restricted Category Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 225 (November 22, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 225 (November 22, 2016)
| Page Range | 83660-83662 | |
| FR Document | 2016-27767 |
[Federal Register Volume 81, Number 225 (Tuesday, November 22, 2016)] [Rules and Regulations] [Pages 83660-83662] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-27767] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3820; Directorate Identifier 2014-SW-024-AD; Amendment 39-18716; AD 2016-23-09] RIN 2120-AA64 Airworthiness Directives; Various Restricted Category Helicopters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for various restricted category helicopters. This AD requires cleaning and visually inspecting certain main rotor (M/R) blades and, depending on the outcome of the inspections, repairing or replacing the M/R blades. This AD was prompted by a report of an M/R blade with multiple fatigue cracks around the blade retention bolt hole. The actions are intended to detect a crack in the M/R blade, and prevent failure of the M/R blade and subsequent loss of helicopter control. DATES: This AD is effective December 27, 2016. ADDRESSES: 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 a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. 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- 3820; 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 AD, the economic evaluation, any comments received, and other information. The street address for [[Page 83661]] the Docket Operations Office (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations Office, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone 817-222-5140; email [email protected]. SUPPLEMENTARY INFORMATION: Discussion On April 11, 2016, at 81 FR 21288, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Model TH-1F, UH-1B, UH- 1F, UH-1H, and UH-1P helicopters with a M/R blade, part number 204-011- 250-005 or 204-011-250-113, installed. The NPRM proposed to require repetitively cleaning and visually inspecting the M/R blades for a crack, corrosion, an edge void, loose or damaged adhesion, and an edge delamination. Depending on the outcome of the inspections, the NPRM proposed repairing or replacing the M/R blades. The actions in the NPRM were prompted by a Bell Helicopter Textron Inc. evaluation of an M/R blade installed on a Model UH-1H helicopter that had 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. A different part-numbered M/R blade of the same type installed on the Model UH-1H helicopter may also be installed on Model TH-1F, UH- 1B, UH-1F, and UH-1P helicopters. These actions are intended to detect a crack in an M/R blade, and prevent failure of the M/R blade, and subsequent loss of helicopter control. Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (81 FR 21288, April 11, 2016). FAA's Determination We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Related Service Information Bell Helicopter issued 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. Bell Helicopter Textron also issued 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 call for visually inspecting the M/R blades during each daily inspection and repetitively washing the blades and applying WD-40. 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, or within 150 hours or 30 days, whichever occurs first, if the blades have more 1,000 hours of operation or have been in service more than 12 months. While ASB No. 204-75-1 and ASB No. 205-75-5 do not apply to the helicopters that are the subject of this AD, they do apply to the affected M/R blades. Differences Between This AD and the Service Information ASB No. UH-1H-13-09 specifies a one-time inspection and then a second repetitive inspection daily and at every 150 hours TIS, and ASB No. 204-75-1 and ASB 205-75-5 call for visually inspecting the M/R blades daily and every 1,000 hours TIS or 12 months, whichever occurs first. This AD requires all inspections at intervals not to exceed 25 hours TIS or two weeks, whichever occurs first. This AD contains more detailed inspection requirements and a more specific inspection area than the instructions in ASB No. UH-1H-13-09. Lastly, ASB No. UH-1H-13- 09 applies to Model UH-1H helicopters with M/R blade P/N 204-011-250- 113, ASB No. 204-75-1 applies to Model 204B helicopters with M/R blade P/N 204-011-250 (all dash numbers), and ASB No. 205-75-5 applies to Model 205A-1 helicopters with M/R blade P/N 204-011-250 (all dash numbers). This AD applies to Model TH-1F, UH-1B, UH-1F, UH-1H, and UH- 1P helicopters with M/R blade P/N 204-011-250-005 or 204-011-250-113. Costs of Compliance We estimate that this AD affects 607 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) requires a total of \1/2\ work-hour. No parts are needed. At an estimated 24 inspections a year, the cost would be $1,032 per helicopter and $626,424 for the U.S. fleet. Replacing an M/R blade requires 12 work hours while parts 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 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 above, 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 [[Page 83662]] 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): 2016-23-09 Various Restricted Category Helicopters: Amendment 39- 18716; Docket No. FAA-2015-3820; Directorate Identifier 2014-SW-024- AD. (a) Applicability This AD applies to Model TH-1F, UH-1B, UH-1F, UH-1H, and UH-1P helicopters with a main rotor (M/R) blade, part number 204-011-250- 005 or 204-011-250-113, installed. (b) Unsafe Condition This AD defines the unsafe condition as a crack in an M/R blade, which could result in failure of the M/R blade and subsequent loss of helicopter control. (c) Effective Date This AD becomes effective December 27, 2016. (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 area 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 entire 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. (f) Special Flight Permits Special flight permits are prohibited. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort Worth, Texas 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. (h) Additional Information Bell Helicopter Alert Service Bulletin (ASB) No. UH-1H-13-09, dated January 14, 2013, and Bell Helicopter Textron ASB No. 204-75-1 and ASB 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 final rule. 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 a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177. (i) Subject Joint Aircraft Service Component (JASC) Code: 6210, Main Rotor Blades. Issued in Fort Worth, Texas, on November 4, 2016. Lance T. Gant, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016-27767 Filed 11-21-16; 8:45 am] BILLING CODE 4910-13-P
![83660 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations
ST00830SE is installed, a ‘‘change in modification, or alteration required by this Issued in Renton, Washington, on October
product’’ alternative method of compliance AD if it is approved by the Boeing 21, 2016.
(AMOC) approval request is not necessary to Commercial Airplanes Organization Michael Kaszycki,
comply with the requirements of 14 CFR Designation Authorization (ODA) that has Acting Manager, Transport Airplane
39.17. been authorized by the Manager, Seattle Directorate, Aircraft Certification Service.
(d) Subject ACO, to make those findings. To be
[FR Doc. 2016–26621 Filed 11–21–16; 8:45 am]
approved, the repair method, modification
Air Transport Association (ATA) of deviation, or alteration deviation must meet BILLING CODE 4910–13–P
America Code 53, Fuselage. the certification basis of the airplane, and the
(e) Unsafe Condition approval must specifically refer to this AD.
(4) For service information that contains DEPARTMENT OF TRANSPORTATION
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating steps that are labeled as Required for
Compliance (RC), the provisions of Federal Aviation Administration
that the stringer (S)–14L and S–14R lap
splices are subject to widespread fatigue paragraphs (i)(4)(i) and (i)(4)(ii) of this AD
damage (WFD). We are issuing this AD to apply. 14 CFR Part 39
detect and correct widespread cracking in the (i) The steps labeled as RC, including
[Docket No. FAA–2015–3820; Directorate
S–14L and S–14R lap splices that could substeps under an RC step and any figures Identifier 2014–SW–024–AD; Amendment
rapidly link up and result in possible rapid identified in an RC step, must be done to 39–18716; AD 2016–23–09]
decompression and reduced structural comply with the AD. If a step or substep is
integrity of the airplane. labeled ‘‘RC Exempt,’’ then the RC RIN 2120–AA64
requirement is removed from that step or
(f) Compliance
substep. An AMOC is required for any Airworthiness Directives; Various
Comply with this AD within the deviations to RC steps, including substeps Restricted Category Helicopters
compliance times specified, unless already and identified figures.
done. (ii) Steps not labeled as RC may be AGENCY: Federal Aviation
(g) Repetitive Inspections deviated from using accepted methods in Administration (FAA), DOT.
At the applicable compliance time accordance with the operator’s maintenance ACTION: Final rule.
specified in paragraph 1.E., ‘‘Compliance,’’ of or inspection program without obtaining
Boeing Alert Service Bulletin 737–53A1352, approval of an AMOC, provided the RC steps, SUMMARY: We are adopting a new
Revision 1, dated March 10, 2016, do a low including substeps and identified figures, can airworthiness directive (AD) for various
frequency eddy current inspection for still be done as specified, and the airplane restricted category helicopters. This AD
cracking of the lower fastener row of S–14L can be put back in an airworthy condition. requires cleaning and visually
and S–14R lap splices, in accordance with (j) Related Information inspecting certain main rotor (M/R)
the Accomplishment Instructions of Boeing blades and, depending on the outcome
Alert Service Bulletin 737–53A1352, For more information about this AD,
contact Gaetano Settineri, Aerospace
of the inspections, repairing or replacing
Revision 1, dated March 10, 2016. Repeat the
inspection thereafter at the applicable times Engineer, Airframe Branch, ANM–120S, the M/R blades. This AD was prompted
specified in paragraph 1.E., ‘‘Compliance,’’ of FAA, Seattle ACO, 1601 Lind Avenue SW., by a report of an M/R blade with
Boeing Alert Service Bulletin 737–53A1352, Renton, WA 98057–3356; phone: 425–917– multiple fatigue cracks around the blade
Revision 1, dated March 10, 2016. If any 6577; fax: 425–917–6590; email: retention bolt hole. The actions are
cracking is found, before further flight, repair gaetano.settineri@faa.gov. intended to detect a crack in the M/R
using a method approved in accordance with blade, and prevent failure of the M/R
the procedures specified in paragraph (i) of (k) Material Incorporated by Reference
blade and subsequent loss of helicopter
this AD. (1) The Director of the Federal Register control.
approved the incorporation by reference
(h) Credit for Previous Actions DATES: This AD is effective December
(IBR) of the service information listed in this
This paragraph provides credit for the paragraph under 5 U.S.C. 552(a) and 1 CFR 27, 2016.
actions required by paragraph (g) of this AD, part 51. ADDRESSES: For service information
if those actions were performed before the (2) You must use this service information identified in this final rule, contact Bell
effective date of this AD using Boeing Alert as applicable to do the actions required by
Service Bulletin 737–53A1352, dated October
Helicopter Textron, Inc., P.O. Box 482,
this AD, unless the AD specifies otherwise. Fort Worth, TX 76101; telephone (817)
2, 2015. (i) Boeing Alert Service Bulletin 737– 280–3391; fax (817) 280–6466; or at
(i) Alternative Methods of Compliance 53A1352, Revision 1, dated March 10, 2016.
http://www.bellcustomer.com/files/.
(AMOCs) (ii) Reserved.
(3) For service information identified in
You may review a copy of the
(1) The Manager, Seattle Aircraft referenced service information at the
Certification Office (ACO), FAA, has the this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data FAA, Office of the Regional Counsel,
authority to approve AMOCs for this AD, if
Services (C&DS), 2600 Westminster Blvd., Southwest Region, 10101 Hillwood
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19, MC 110–SK57, Seal Beach, CA 90740; Pkwy, Room 6N–321, Fort Worth, TX
send your request to your principal inspector telephone 562–797–1717; Internet https:// 76177.
or local Flight Standards District Office, as www.myboeingfleet.com.
(4) You may view this service information Examining the AD Docket
appropriate. If sending information directly
to the manager of the ACO, send it to the at the FAA, Transport Airplane Directorate, You may examine the AD docket on
attention of the person identified in 1601 Lind Avenue SW., Renton, WA. For the Internet at http://
paragraph (j) of this AD. Information may be information on the availability of this www.regulations.gov by searching for
emailed to: 9-ANM-Seattle-ACO-AMOC- material at the FAA, call 425–227–1221. and locating Docket No. FAA–2015–
sradovich on DSK3GMQ082PROD with RULES
Requests@faa.gov. (5) You may view this service information
3820; or in person at the Docket
(2) Before using any approved AMOC, that is incorporated by reference at the
National Archives and Records Operations Office between 9 a.m. and 5
notify your appropriate principal inspector,
or lacking a principal inspector, the manager Administration (NARA). For information on p.m., Monday through Friday, except
of the local flight standards district office/ the availability of this material at NARA, call Federal holidays. The AD docket
certificate holding district office. 202–741–6030, or go to: http:// contains this AD, the economic
(3) An AMOC that provides an acceptable www.archives.gov/federal-register/cfr/ibr- evaluation, any comments received, and
level of safety may be used for any repair, locations.html. other information. The street address for
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![83662 Federal Register / Vol. 81, No. 225 / Tuesday, November 22, 2016 / Rules and Regulations
under the criteria of the Regulatory blade skin for a crack and any corrosion. Pay (f) Special Flight Permits
Flexibility Act. particular attention for any cracking in a Special flight permits are prohibited.
We prepared an economic evaluation doubler or skin near or at the same blade
station as the blade retention bolt hole (blade (g) Alternative Methods of Compliance
of the estimated costs to comply with (AMOCs)
station 28).
this AD and placed it in the AD docket. (iii) Visually inspect the exposed areas of (1) The Manager, Rotorcraft Certification
List of Subjects in 14 CFR Part 39 each bond line at the edges of the lower grip Office, FAA, may approve AMOCs for this
pad, upper and lower grip plates, and each AD. Send your proposal to: Charles Harrison,
Air transportation, Aircraft, Aviation layered doubler (bond lines) on the upper Project Manager, Fort Worth Aircraft
safety, Incorporation by reference, and lower surfaces of each M/R blade for the Certification Office, 10101 Hillwood Pkwy.,
Safety. entire length and chord width for an edge Fort Worth, Texas 76177; telephone 817–
void, any corrosion, loose or damaged 222–5140; email 9-ASW-FTW-AMOC-
Adoption of the Amendment adhesive squeeze-out, and an edge Requests@faa.gov.
Accordingly, under the authority delamination. Pay particular attention to any (2) For operations conducted under a 14
delegated to me by the Administrator, crack in the paint finish that follows the CFR part 119 operating certificate or under
the FAA amends 14 CFR part 39 as outline of a grip pad, grip plate, or doubler, 14 CFR part 91, subpart K, we suggest that
and to any loose or damaged adhesive you notify your principal inspector, or
follows:
squeeze-out, as these may be the indication lacking a principal inspector, the manager of
of an edge void. the local flight standards district office or
PART 39—AIRWORTHINESS
(2) If there is a crack, any corrosion, an certificate holding district office before
DIRECTIVES edge void, loose or damaged adhesive operating any aircraft complying with this
squeeze-out, or an edge delamination during AD through an AMOC.
■ 1. The authority citation for part 39 any inspection in paragraph (e)(1) of this AD,
continues to read as follows: before further flight, do the following: (h) Additional Information
Authority: 49 U.S.C. 106(g), 40113, 44701. (i) If there is a crack in a grip pad or any Bell Helicopter Alert Service Bulletin
grip plate or doubler, replace the M/R blade (ASB) No. UH–1H–13–09, dated January 14,
§ 39.13 [Amended] with an airworthy M/R blade. 2013, and Bell Helicopter Textron ASB No.
■ 2. The FAA amends § 39.13 by adding (ii) If there is a crack in the M/R blade skin 204–75–1 and ASB 205–75–5, both Revision
the following new airworthiness that is within maximum repair damage C and both dated April 25, 1979, which are
limits, repair the M/R blade. If the crack not incorporated by reference, contain
directive (AD): exceeds maximum repair damage limits, additional information about the subject of
2016–23–09 Various Restricted Category replace the M/R blade with an airworthy M/ this final rule. For service information
Helicopters: Amendment 39–18716; R blade. identified in this final rule, contact Bell
Docket No. FAA–2015–3820; Directorate (iii) If there is any corrosion within Helicopter Textron, Inc., P.O. Box 482, Fort
Identifier 2014–SW–024–AD. maximum repair damage limits, repair the M/ Worth, TX 76101; telephone (817) 280–3391;
(a) Applicability R blade. If the corrosion exceeds maximum fax (817) 280–6466; or at http://
repair damage limits, replace the M/R blade www.bellcustomer.com/files/. You may
This AD applies to Model TH–1F, UH–1B, with an airworthy M/R blade. review a copy of this service information at
UH–1F, UH–1H, and UH–1P helicopters with (iv) If there is an edge void in the grip pad the FAA, Office of the Regional Counsel,
a main rotor (M/R) blade, part number 204– or in a grip plate or doubler, determine the Southwest Region, 10101 Hillwood Pkwy.,
011–250–005 or 204–011–250–113, installed. length and depth using a feeler gauge. Repair Room 6N–321, Fort Worth, TX 76177.
(b) Unsafe Condition the M/R blade if the edge void is within
maximum repair damage limits, or replace (i) Subject
This AD defines the unsafe condition as a
the M/R blade with an airworthy M/R blade. Joint Aircraft Service Component (JASC)
crack in an M/R blade, which could result in
(v) If there is an edge void in a grip plate Code: 6210, Main Rotor Blades.
failure of the M/R blade and subsequent loss
or doubler near the outboard tip, tap inspect Issued in Fort Worth, Texas, on November
of helicopter control.
the affected area to determine the size and 4, 2016.
(c) Effective Date shape of the void. Repair the M/R blade if the Lance T. Gant,
This AD becomes effective December 27, edge void is within maximum repair damage
limits, or replace the M/R blade with an Manager, Rotorcraft Directorate, Aircraft
2016. Certification Service.
airworthy M/R blade.
(d) Compliance (vi) If there is any loose or damaged [FR Doc. 2016–27767 Filed 11–21–16; 8:45 am]
You are responsible for performing each adhesive squeeze-out along any of the bond BILLING CODE 4910–13–P
action required by this AD within the lines, trim or scrape away the adhesive
specified compliance time unless it has without damaging the adjacent surfaces or
already been accomplished prior to that time. parent material of the M/R blade. Determine
DEPARTMENT OF TRANSPORTATION
if there is an edge void or any corrosion by
(e) Required Actions lightly sanding the trimmed area smooth
Federal Aviation Administration
(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
thereafter at intervals not to exceed 25 hours area. 14 CFR Part 39
TIS or 2 weeks, whichever occurs first, clean (vii) If there is an edge delamination along [Docket No. FAA–2016–4223; Directorate
the upper and lower exposed surfaces of each any of the bond lines or a crack in the paint Identifier 2015–NM–108–AD; Amendment
M/R blade from an area starting at the butt finish, determine if there is an edge void or 39–18693; AD 2016–22–04]
end of the blade to three inches outboard of a crack in the grip pad, grip plate, doubler,
the doublers. Using a 3X or higher power or skin by removing paint from the affected RIN 2120–AA64
magnifying glass and a light, inspect as area by lightly sanding in a span-wise
follows: direction using 180–220 grit paper. If there Airworthiness Directives; Gulfstream
sradovich on DSK3GMQ082PROD with RULES
(i) Visually inspect the exposed area of the are no edge voids and no cracks, refinish the Aerospace Corporation Airplanes
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 AGENCY: Federal Aviation
corrosion. during any sanding or trimming in Administration (FAA), DOT.
(ii) On the upper and lower exposed paragraphs (e)(2)(vi) or (e)(2)(vii) of this AD, ACTION: Final rule.
surfaces of each M/R blade from blade repair the M/R blade if the damage is within
stations 24.5 to 35 for the entire chord width, maximum repair damage limits, or replace SUMMARY: We are adopting a new
visually inspect each layered doubler and the M/R blade with an airworthy M/R blade. airworthiness directive (AD) for certain
VerDate Sep<11>2014 17:46 Nov 21, 2016 Jkt 241001 PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 E:\FR\FM\22NOR1.SGM 22NOR1](https://thefederalregister.org/doc/81_FR_83885/page/3.svg)
Document Created: 2018-02-14 08:29:31
Document Modified: 2018-02-14 08:29:31
| 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. | |
| Dates | This AD is effective December 27, 2016. | |
| Contact | Charles Harrison, Project Manager, Fort Worth Aircraft Certification Office, 10101 Hillwood Pkwy., Fort Worth, Texas 76177; telephone 817-222-5140; email [email protected] | |
| FR Citation | 81 FR 83660 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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