WIX Archives
The Entire document.... B17 E, F , G
Posted by Tony on Sun Nov 04, 2001 07:16:00 AM
In reply top Fortresses posted by simon king on Sun Nov 04, 2001 04:45:12 AM
However, the FAA seem to understand the difficulties facing warbird owners, but read the document , it explains it better
Tony :0)
Airworthiness Directives
Header Information
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-15-AD; Amendment 39-12485; AD 2001-22-06]
RIN 2120-AA64
Airworthiness Directives; Boeing Model B-17E, F, and G Airplanes
Preamble Information
Regulatory Information
2001-22-06 Boeing: Amendment 39-12485. Docket 95-NM-15-AD.
Applicability: All Model B-17E, F, and G airplanes, certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Note 2: For airplanes on which the terminal fitting-to-spar chord joints were separated prior to the effective date of this AD, and inspections of and/or repairs to the wing terminals-to-spar chords were accomplished prior to the effective date of this AD: Applications for approval of an alternative method of compliance to the requirements of paragraphs (a) and (b) of this AD must be submitted to the FAA in accordance with the provisions of paragraph (d) of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent reduced structural integrity of the wing of the airplane, accomplish the following:
Inspections and Corrective Actions
(a) Within 180 days after the effective date of this AD, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD.
(1) Perform a dye penetrant inspection to detect cracking of each inboard end of the eight aluminum wing spar chords, in accordance with MIL-STD-6866, using a fluorescent Type 1 penetrant, Method C, Sensitivity Level 3, inspection. If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA.
Note 3: The part number (P/N) for the upper wing spar chords is 3-14231-0, and the P/N for the lower wing spar chords is 3-14231-1.
Note 4: Operators desiring to use an alternative dye penetrant procedure may request approval from the Seattle ACO in accordance with paragraph (d) of this AD.
Note 5: The following are the P/N's for the terminal fitting-to-spar chord joint assemblies:
Assemblies Assembly part number
Left Upper Front Spar Joint Assembly 75-4781-0
Right Upper Front Spar Joint Assembly 75-4781-1
Left Lower Front Spar Joint Assembly 65-4782-512
Right Lower Front Spar Joint Assembly 65-4782-513
Left Upper Rear Spar Joint Assembly 75-4783-0
Right Upper Rear Spar Joint Assembly 75-4783-1
Left Lower Rear Spar Joint Assembly 75-4784-0
Right Lower Rear Spar Joint Assembly 75-4784-1
Note 6: The following are the P/N's for the bolts for the spar chords:
Bolts for: Bolt part number
Upper and Lower Front Spar Chords NAS56A36
Upper Rear Spar Chord NAS56A34
Lower Rear Spar Chord NAS56A40-5
(2) Perform a detailed visual inspection to detect corrosion of the bolts, as installed, and replace any corroded bolt with a new bolt having a P/N in the NAS 6606 series in accordance with Army Technical Order Number 01-20EF-2. Prior to further flight, for all bolt replacements, accomplish the requirements of paragraphs (a)(2)(i), (a)(2)(ii), (a)(2)(iii), and (a)(2)(iv) of this AD in accordance with Army Technical Order Number 01-20EF-2.
Note 7: The following are the P/N's for the replacement bolts for the spar chords:
Replacement bolts for: Replacement bolt part number
Upper and Lower Front Spar NAS 6606-51
Upper Rear Spar NAS 6606-47
Lower Rear Spar NAS 6606-56
Note 8: For the purposes of this AD, a detailed visual inspection is defined as: "An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required."
(i) Install a washer having P/N MS 20002C6 under the head of the bolt, a self-locking nut having P/N NAS 1804-6, and a washer having P/N MS 200026 under the nut, for each replacement bolt.
(ii) Torque any replacement bolt to 95-105 inch-pounds.
(iii) Oversize replacement bolts by 1/16 inch, as necessary.
(iv) Apply corrosion inhibiting compound (using BMS 3-23, Type II or equivalent compound) to the spar chord after bolt removal, replacement, or other remedial action.
(b) Within 18 months after the effective date of this AD, accomplish the requirements of either paragraph (b)(1) or (b)(2) of this AD.
(1) Perform detailed visual and high frequency eddy current inspections, that include separating all eight wing terminal-to-spar chord joints, to detect cracking and corrosion of the wing terminals and spar chords, in accordance with a method approved by the Manager, Seattle ACO; or
(2) Accomplish either paragraph (b)(2)(i) or (b)(2)(ii) of this AD.
(i) Perform an equivalent inspection(s) to that required by paragraph (b)(1) of this AD in accordance with a method approved by the Manager, Seattle ACO. To be considered acceptable, the equivalent inspection(s) must include, at a minimum, the criteria specified in paragraphs (b)(2)(i)(A), (b)(2)(i)(B), and (b)(2)(i)(C) of this AD.
(A) The inspection must include removal of all 64 bolts that join the eight wing terminals to the eight spar chords; and
(B) The inspection must adequately detect cracking of the spar chord, and corrosion between the terminal fitting and the spar chord; and
(C) The inspection must include a detailed visual inspection to detect corrosion of the attachment bolts; and a high frequency eddy current, and borescope inspection at 10-power magnification, of the bolt holes common to the spar chord-to-wing terminal interface.
(ii) Perform a dye penetrant inspection to detect cracking of the spar chord tube end; remove the most outboard five bolts in the joint and perform an eddy current inspection to detect cracking of the holes; and perform a 10-power magnification borescope inspection to detect corrosion of the most inboard three bolts. If the criteria specified in paragraphs (b)(2)(ii)(A), (b)(2)(ii)(B), and (b)(2)(ii)(C) of this AD are met, removal of the three most inboard bolts of each terminal-to-spar chord joint is not required. Repeat the requirements of this paragraph thereafter at intervals not to exceed 36 months.
(A) Results of the dye penetrant inspection of the spar chord tube end indicate that there is no cracking; and
(B) Results of the eddy current inspection indicate that the holes of the five most outboard bolts in the joint are free of cracks; and
(C) Results of the 10-power magnification borescope inspection indicate that the most inboard three bolts are free of corrosion.
Note 9: The Boeing Company will make its specifications for eddy current inspections available to operators as needed.
(c) If any cracking and/or corrosion is detected during any of the inspections required by paragraphs (a) and (b) of this AD, prior to further flight, repair in accordance with a method approved by the Manager, Seattle ACO.
Alternative Methods of Compliance
(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Seattle ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO.
Note 10: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.
Note 11: The FAA strongly encourages owners and operators of the affected airplanes to coordinate their requests for approvals of alternative methods of compliance or adjustment of the compliance times pertaining to this AD. Coordination of a single request (in lieu of a separate request from each owner/operator) will allow the FAA to more quickly review and respond.
Special Flight Permits
(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
Effective Date
(f) This amendment becomes effective on November 30, 2001.
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