AD 84-15-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | P. V. Shields | A-26B (Army) | Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes |
| aircraft | P. V. Shields | A-26C (Army) | Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes |
Unsafe Condition
Failure of a lower spar cap due to cracking or fretting in the area where the nacelle fairing upper edge contacts the lower spar cap surface.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform a visual dye penetrant inspection of the lower forward and aft spar cap areas near each nacelle. Trim the fairing edge to ensure smoothness and 1/16 inch clearance. Repeat inspections at intervals not exceeding 500 hours or 30 hours if damage is found. Polish damaged areas up to 0.030 inches deep and report results within 72 hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within ten (10) hours time in service after the effective date of this AD
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Douglas Aircraft Model A-26/B26 series airplanes certificated in all categories, including A-26B (Army) and A-26C (Army) models.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Wing Inflight Structure
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_84-15-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-15-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes Subject: Wing Inflight Structure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/16/1985 Make: P. V. Shields Model: A-26B (Army) | A-26C (Army) Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 84-15-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5031 AD NUMBER: 84-15-02 SUBJECT HEADING: Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes ACTION: SUMMARY: DATES: Effective April 16, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-15-02 DOUGLAS AIRCRAFT COMPANY: Amendment 39-5031. Applies to Douglas Aircraft Model A-26/B26 series airplanes certificated in all categories. Compliance schedule as prescribed in the body of the AD, unless previously accomplished. To prevent loss of wing structural integrity due to failure of a lower spar cap, accomplish the following: A. Within ten (10) hours time in service after the effective date of this AD, perform a visual dye penetrant inspection of the lower forward and aft spar cap, outboard and inboard of each nacelle in the area where the nacelle fairing upper edge runs across the lower spar cap surface. Trim the fairing edge if necessary, to ensure that the fairing edge is smooth and that there is a minimum of one-sixteenth inch (1/16") clearance between the fairing and spar cap surface. B. If no cracking or fretting of the spar cap is detected, repeat the inspection for cracks, surface clearance, and condition in accordance with Paragraph A. of this AD at intervals not to exceed 500 hours time in service. C. If any evidence of cracking or fretting is found in the spar caps, polish out to a machine finish not to exceed approximately 125 microinches on both sides of the damaged area to a maximum depth of 0.030 inches and repeat the inspection of Paragraph A., above. Continue to inspect in accordance with Paragraph A. at intervals not to exceed 30 hours time in service. D. If cracking or fretting in excess of 0.030 inches in a spar cap is detected, repair in a manner approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. E. For those aircraft which have been modified to incorporate a steel or titanium lower front spar cap strap (in the area where the nacelle fairing upper edge is in contact with the lower wing surface) in accordance with AD 64-12-03, the requirements of Paragraph A. of this AD are applicable only to the lower aft spar cap, outboard and inboard of each nacelle. F. Within 72 hours after performing the inspections required by Paragraph A., above, report the results of the inspections to the Manager, Western Aircraft Certification Office, ANM-170W, FAA, Northwest Mountain Region, 15000 Aviation Blvd., Hawthorne, California. Mailing address: P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. The reports should cite the airplane registration and serial number, crack location and extent of damage, total airplane operating hours, and time since last inspection. G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. H. Alternate inspections, modifications, or other actions which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. This amendment becomes effective April 16, 1985, and it was effective earlier to all recipients of priority mail AD 84-15-02, issued August 1, 1984. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_84-15-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-15-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes Subject: Wing Inflight Structure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 04/16/1985 Make: P. V. Shields Model: A-26B (Army) | A-26C (Army) Product Type: Aircraft Product Subtype: 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: 84-15-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-5031 AD NUMBER: 84-15-02 SUBJECT HEADING: Airworthiness Directives; DOUGLAS A-26/B26 Series Airplanes ACTION: SUMMARY: DATES: Effective April 16, 1985. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-15-02 DOUGLAS AIRCRAFT COMPANY: Amendment 39-5031. Applies to Douglas Aircraft Model A-26/B26 series airplanes certificated in all categories. Compliance schedule as prescribed in the body of the AD, unless previously accomplished. To prevent loss of wing structural integrity due to failure of a lower spar cap, accomplish the following: A. Within ten (10) hours time in service after the effective date of this AD, perform a visual dye penetrant inspection of the lower forward and aft spar cap, outboard and inboard of each nacelle in the area where the nacelle fairing upper edge runs across the lower spar cap surface. Trim the fairing edge if necessary, to ensure that the fairing edge is smooth and that there is a minimum of one-sixteenth inch (1/16") clearance between the fairing and spar cap surface. B. If no cracking or fretting of the spar cap is detected, repeat the inspection for cracks, surface clearance, and condition in accordance with Paragraph A. of this AD at intervals not to exceed 500 hours time in service. C. If any evidence of cracking or fretting is found in the spar caps, polish out to a machine finish not to exceed approximately 125 microinches on both sides of the damaged area to a maximum depth of 0.030 inches and repeat the inspection of Paragraph A., above. Continue to inspect in accordance with Paragraph A. at intervals not to exceed 30 hours time in service. D. If cracking or fretting in excess of 0.030 inches in a spar cap is detected, repair in a manner approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. E. For those aircraft which have been modified to incorporate a steel or titanium lower front spar cap strap (in the area where the nacelle fairing upper edge is in contact with the lower wing surface) in accordance with AD 64-12-03, the requirements of Paragraph A. of this AD are applicable only to the lower aft spar cap, outboard and inboard of each nacelle. F. Within 72 hours after performing the inspections required by Paragraph A., above, report the results of the inspections to the Manager, Western Aircraft Certification Office, ANM-170W, FAA, Northwest Mountain Region, 15000 Aviation Blvd., Hawthorne, California. Mailing address: P.O. Box 92007, Worldway Postal Center, Los Angeles, California 90009. The reports should cite the airplane registration and serial number, crack location and extent of damage, total airplane operating hours, and time since last inspection. G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD. H. Alternate inspections, modifications, or other actions which provide an acceptable level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, Hawthorne, California. This amendment becomes effective April 16, 1985, and it was effective earlier to all recipients of priority mail AD 84-15-02, issued August 1, 1984. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
64-12-03
final ruleAirworthiness Directives; DOUGLAS Models A-26B and A-26C
Unsafe Condition: Failure of the wing rear spar caps in the vicinity of the flap inboard hinges and failure of the wing rear spar lower caps near the inboard end of the fore and aft flanges and the forward flange 3/...
61-11-05
final ruleAirworthiness Directives; DOUGLAS All Models A-26 (B-26) Series Aircraft
Unsafe Condition: Severe corrosion of the wing structure beneath the wing fuel tanks and deterioration of sponge rubber mats under fuel cells.
55-26-01
final ruleAirworthiness Directives; DOUGLAS A-26 Aircraft
Unsafe Condition: Explosion in the air due to potential fuel tank fumes ignition in the rear fuselage fuel tank compartment.
56-18-03
final ruleAirworthiness Directives; DOUGLAS All Models A-26B and A-26C Aircraft
Unsafe Condition: Cracks in the nose gear cross beam assembly at the inboard end of the trunnion journal.
