AD 72-15-01

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AD Number:
72-15-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Hawker Siddeley Aviation LTD Model DH-114 Heron Airplanes
Subject:
Wing to Fuselage Attach Bolts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/11/1972
Make:
de Havilland Aircraft Co., Ltd., The
Model:
D.H.114 Heron Series 2A | D.H.114 Heron Series 2DA | D.H.114 Heron Series 2X
Product Type:
Aircraft
Product Subtype:
Small/Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 72-15-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1483

AD NUMBER:   72-15-01

SUBJECT HEADING:   Airworthiness Directives; Hawker Siddeley Aviation LTD Model DH-114 Heron Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 11, 1972.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
72-15-01 HAWKER SIDDELEY AVIATION LTD.: Amendment 39-1483. Applies to deHavilland "Heron" Model DH-114 airplanes.

To prevent a possible failure of the wing to fuselage attachment, accomplish the following:

(a) Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished in accordance with one of the AD's specified in subparagraph (a)(4), comply with subparagraphs (a)(1), (a)(2), and (a)(3), and thereafter comply with subparagraph (a)(2) at intervals not to exceed six years from the last inspection and with (a)(3) at intervals not to exceed 4,500 hours' time in service from the last inspection.

(1) Inspect the bore of the wing main spar lower pick-up fittings for chrome plating in accordance with Appendix 1 of Hawker Siddeley Aviation Limited Technical News Sheet, Series: Heron (114) No. W. 17, Issue 1, dated July, 7, 1970, or an FAA-approved equivalent. If a bore is found to be chrome plated, before further flight, replace the affected fitting with a serviceable fitting that does not have a chrome plated bore.

(2) Inspect the wing main spar lower pick-up fittings, the fuselage center section spar boom lugs, and the main wing to fuselage lower attachment bolts for corrosion, surface roughness, and signs of fretting in accordance with Appendix 1 of Hawker Siddeley Aviation Limited, Technical News Sheet, Series: Heron (114), No. W. 9, Issue 5, dated July 12, 1971, or an FAA-approved equivalent.

(3) Inspect the total length of the bore of the wing main spar lower pick-up fittings for cracks in accordance with Appendix 2 of Hawker Siddeley Aviation Limited, Technical News Sheet, Series: Heron (114), No. W.9 (referred to above), or on FAA-approved equivalent. Eddy Current equipment, of a manufacture not specified in the referenced service bulletin, may be used to comply with this subparagraph, if the equipment meets the sensitivity requirement contained in the referenced service bulletin, the equipment is suitable for inspection of ferrous materials, and the procedure used to operate the equipment complies with the equipment manufacturer's recommended operating instructions.

(4) Previous AD's on this same subject which may be used in establishing compliance with the initial inspection specified in paragraph (a) are: AD 70-15-11, Amendment 39-1041 issued July 13, 1970, as amended by Amendment 39-1186 issued March 31, 1971; AD 70-12-09, Amendment 39-1010, dated June 8, 1970; AD 70-05-04, Amendment 39-948, dated May 28, 1970; and the telegraphic AD's dated May 28, 1970, and June 11, 1970.

(b) Each time the wing to fuselage lower joint is reassembled after any inspection required by this AD or for any other reason, apply corrosion protection in accordance with Appendix 1 of Hawker Siddeley Aviation Limited, Technical News Sheet, Series: Heron (114) No. W. 9 (referred to above), or an FAA-approved equivalent.

(c) If during the inspections required by subparagraphs (a)(2) or (a)(3), corrosion, pitting, fretting, or corrosion discoloration is found which cannot be removed using the procedures in Appendix 1 of Hawker Siddeley Aviation Limited, Technical News Sheets, Series: Heron (114), No. W. 9 (referred to above), or an FAA-approved equivalent, or if cracks are found in the wing main spar pick-up fitting bore, before further flight, replace the affected part with a serviceable part of the same part number except as provided in paragraphs (d), (e) and (f) of this AD.

(d) If during the inspections required by paragraph (a), the following obsolete main wing to fuselage lower attachment bolts are found, before further flight, replace the obsolete bolts with the appropriate replacement bolts listed below:
Obsolete Bolt P/Ns	Replacement Bolt P/Ns

14.FS.15	14FS.6669
14.FS.3985	14FS.6669
14.FS.6399	14FS.6669
14.2FS.1555	14.2FS.575
RD.14W.173ND	RD.14FS.274
RD.14W.175ND	RD.14FS.275
RD.14FS.262	RD.14FS.271
RD.14FS.259	RD.14FS.272
RD.14FS.260	RD.14FS.273
RD.14FS.165	RD.14FS.273

(e) If during the inspections required by paragraph (a), the following obsolete main wing to fuselage lower attachment bolts are found, before further flight, ream the wing center section spar boom lugs and main spar lower pick-up fittings in accordance with Hawker Siddeley Repair Drawings RD.14FS.263 and RD.14FS.270 or FAA-approved equivalents and replace the obsolete bolts with the appropriate replacement bolts listed below:
ObsoleteBolt P/Ns	Replacement Bolt P/Ns

RD.14FS.254	RD.14FS.271
RD.14FS.232	RD.14FS.272
RD.14FS.223	RD.14FS.273

(f) If during the inspections required by paragraph (a), main wing to fuselage lower attachment bolts are found which are other than those listed as either obsolete or replacement bolts in paragraphs (c) and (d), before further flight, report the part number for the installed bolts to the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region to obtain the identification of the required replacement bolts (reporting approved by the Bureau of the Budget under BOB No. 04.R 0174). Upon receipt of notice giving the part number of the required replacement bolts, install the replacement bolts specified in the notification.

This amendment supersedes Amendment 39-1041 (35 F. R. 11554), AD 70-15-11 as amended by Amendment 39-1186 (36 F.R. 5967).

This amendment becomes effective July 11, 1972.

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