2012-02-10: Stabilizers

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 removing airworthiness directive (AD) 2011-07-13, Amendment 39-16650 (76 FR 18376, April 4, 2011), and adding the following new AD: 2012-02-10 CPAC, Inc. (Type Certificate Formerly Held by Commander Aircraft Corporation, Gulfstream Aerospace [[Page 6665]] Corporation, and Rockwell International): Amendment 39-16933; Docket No. FAA-2011-1128; Directorate Identifier 2011-CE-031-AD. (a) Effective Date This airworthiness directive (AD) is effective March 15, 2012. (b) Affected ADs This AD supersedes AD 2011-07-13, Amendment 39-16650 (76 FR 18376, April 4, 2011). (c) ApplicabilityThis AD applies to CPAC, Inc. (type certificate formerly held by Commander Aircraft Corporation, Gulfstream Aerospace Corporation, and Rockwell International) Models 112, 112B, 112TC, 112TCA, 114, 114A, 114B, and 114TC airplanes, all serial numbers, certificated in any category. Type Certificate No. A12SO does not include Models 112A and 115. The Model 112A is a Rockwell ``marketing name'' for the Model 112. The Model 115 is a Rockwell ``marketing name'' for the Model 114. Since they are type-certificated as Model 112 and Model 114, this AD is applicable to the Models 112A and 115. (d) Subject Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of a total of nine elevator spar cracks across seven of the affected airplanes, including a crack of 2.35 inches just below the outboard hinge of the right-hand elevator. We are issuing this AD to prevent structural failure of the elevator spar due to such cracking, which could result in separation of the elevator from the airplane with consequent loss of control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. The inspection intervals and procedures in this AD take precedence over those contained in Parts Manufacturer Approval (PMA) Elevator Spars 44211-RE9 and 44211-RE10, Instructions for Continued Airworthiness, original issue date May 5, 2011. (g) Inspection Requirement Retained From AD 2011-07-13, Amendment 39- 16650 (76 FR 18376, April 4, 2011) Within the next 5 hours time-in-service (TIS) after April 4, 2011 (the effective date retained from AD 2011-07-13 (76 FR 18376, April 4, 2011)), visually inspect the left-hand (LH) and right-hand (RH) elevator spar behind and around the outboard hinge bracket on the elevator spar for cracks. Do the inspection following the procedures specified in paragraph (j) of this AD. If cracks are found during this inspection, take the necessary corrective actions specified in paragraph (k) of this AD. (h) Reporting Requirement Retained From AD 2011-07-13, Amendment 39- 16650 (76 FR 18376, April 4, 2011) Within 30 days after the inspection required in paragraph (g) of this AD, report the results of the inspection to the FAA, Wichita Aircraft Certification Office (ACO), Attn: T.N. Baktha, Senior Aerospace Engineer, 1801 Airport Road, Room 100; Wichita, Kansas 67209; phone: (316) 946-4155; fax: (316) 946-4107; email: t.n.baktha@faa.gov. Include the following information: (1) Airplane model and serial number. (2) Hours TIS at time of inspection. (3) Annotate any cracking found, including the exact location and length of any cracks. (4) Any installations, repairs, modifications, etc. that have been done on your airplane in the elevator spar area or that could have affected the elevator spar. (5) Type of operation primarily flown. (i) Repetitive Inspection Requirement As a result of the inspection required in paragraph (g) of this AD, if the elevator spar was: (1) Replaced with a new elevator spar, within the next 300 hours TIS after the replacement, visually inspect the elevator spar behind the outboard hinge bracket and surrounding area for cracks. Repetitively inspect thereafter at intervals not to exceed 12 months or 150 hours TIS, whichever occurs first. Do the inspection following the procedures specified in paragraph (j) of this AD. (2) Replaced with a serviceable elevator spar (one that was in service before and had no cracks and/or corrosion), within the next 150 hours TIS after the replacement, visually inspect the elevator spar behind the outboard hinge bracket and surrounding area for cracks. Repetitively inspect thereafter at intervals not to exceed 12 months or 150 hours TIS, whichever occurs first. Do the inspection following the procedures specified in paragraph (j) of this AD. (3) Found free of cracks, within the next 150 hours TIS after the inspection, visually inspect the elevator spar behind the outboard hinge bracket and surrounding area for cracks. Repetitively inspect thereafter at intervals not to exceed 12 months or 150 hours TIS, whichever occurs first. Do the inspection following the procedures specified in paragraph (j) of this AD. (j) Inspection Procedures (1) Disconnect the elevator trim pushrod at the trim tab. (2) Remove the hinge bolts at the horizontal stabilizer points. (3) Remove six screws and two bolts at the inboard end of the elevator and remove the elevator. (4) Remove all fasteners common to the elevator outboard aft end rib, part number (P/N) 44330, and elevator skin, P/N 44323. (5) Remove the remaining two fasteners common to the elevator outboard aft end rib (P/N 44330) and the elevator spar, P/N 44211. (6) Remove the elevator aft end rib, P/N 44330, to gain access to the aft side of the elevator spar. (7) Remove the four bolts, washers, and nuts that secure the outboard elevator hinge bracket, P/N 44285. (8) Remove elevator hinge bracket, P/N 44285, from the elevator spar. (9) Clean in and around the location of the elevator outboard hinge bracket, outboard elevator hinge, and the outboard elevator hinge bracket (as applicable) on the elevator spar and visually inspect for cracks. Use a 10x magnifier to facilitate the detection of any crack. (k) Corrective Actions (1) If cracks are found during any inspection required in paragraphs (g), (i)(1), (i)(2), or (i)(3) of this AD, before further flight, either replace the elevator spar with a new spar or a serviceable spar that is found free of cracks and/or corrosion or repair/modify the elevator spar following a procedure approved for this AD by the FAA, Wichita ACO; (2) After doing the actions required in paragraph (k)(1) of this AD, before further flight, reassemble the elevator assembly, rebalance the elevator, and reinstall on theairplane following standard repair practices. Ensure elevator rigging is within tolerance, and that the system operates with ease, smoothness, and positiveness appropriate to its function; and (3) After taking corrective action, continue with the repetitive inspections required in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (l) Special Flight Permit (1) Special flight permits are permitted for daytime visual flight rules (VFR) only, restricted to crew, calm weather, reduced speed not to exceed 111 knots calibrated air speed (KCAS), and not to exceed 5 flight hours when cracks are found in the elevator spar if: (i) The cracks are at or near the outboard hinge bracket; (ii) The cracks are 1.25 inches long or less; and (iii) There is no more than one crack on the top and one at the bottom of the hinge bracket. (2) Special flight permits are not allowed if: (i) The crack length is greater than 1.25 inches; or (ii) The number of cracks is more than two.(m) 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 5 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 [[Page 6666]] burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (n) AMOCs(1) The Manager, Wichita ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) AMOCs approved for AD 2011-07-13, Amendment 39-16650 (76 FR 18376, April 4, 2011), are approved for this AD. (o) Related Information For more information about this AD, contact T.N. Baktha, Senior Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; phone: (316) 946-4155; fax: (316) 946-4107; email: t.n.baktha@faa.gov.